Pseudo-noise correlator for GPS spread-spectrum receiver

ABSTRACT

A terrestrial C/A code GPS receiver system digitally samples, filters and stores a segment of 11 half chips of the received composite as a binary number and multiplexes this number for parallel correlation with each of a series of multibit code replicas for the satellites to be tracked. Each of the time delay specific correlation products are accumulated in a cell of a memory matrix so that at least twenty two delays for each satellite may be evaluated each code period providing fast reacquisition, even within a city intersection, as well as correction of multipath tracking and multipath interference. All cells of the memory matrix may be used for an acquisition of a single satellite in about 4 ms. Two satellite tracking, in addition to altitude hold, uses cross track hold alternating with clock hold to update the cross track estimate. Single satellite tracking uses cross track and clock hold together. Navigation data is updated with detected changes in motion including turns.

RELATED APPLICATIONS

This application is a continuation of Ser. No. 09/655,633, filed Sep. 5,2000, now U.S. Pat. No. 6,400,753, which is a divisional of Ser. No.08/846,067, filed Apr. 25, 1997, now U.S. Pat. No. 6,393,046, which is acontinuation-in-part of Ser. Nos. 08/637,457, abandoned; 08/638,021, nowU.S. Pat. No. 5,901,171; 08/637,537, now U.S. Pat. No. 6,041,280, and08/638,882, U.S. Pat. No. 5,897,605, all filed Apr. 25, 1996, now U.S.Pat. No. 5,897,605 and claims the priority of provisional patentapplication No. 60/042,868 filed Mar. 28, 1997.

BACKGROUND OF THE INVENTION

1. Field of the Invention

This invention relates in general to spread spectrum receivers and inparticular to GPS navigation systems such as those used in terrestrialnavigation for cars, trucks and other land vehicles.

2. Description of the Related Art

Car navigation is conventionally performed using highway and street mapsaided, to some degree, by distance measurements from external sensorssuch as odometers. Improvements over the last 10 years in GlobalPositioning System, or GPS, satellite navigation receivers has spawnedseveral GPS car navigation systems.

Conventional GPS car navigation systems use the last known position ofthe vehicle, and the destination data, to compute a route data base,including route and turning data derived from a pre-existing map database. GPS receivers are conventionally operated with a minimum of 3 or 4satellites distributed across the visible sky in order to determine, orat least estimate, the four necessary unknowns including x_(user),y_(user) and z_(user) which provide three orthogonal coordinates tolocate the user as well as t_(user) which provides the requiredsatellite time. Techniques such as time or clock hold and altitude hold,in which the unknown time or altitude is assumed to remain predictablefrom a previously determined value, e.g., z_(est) and/or t _(est), havepermitted operation of GPS receivers with less than four satellites inview. In particular, terrestrial GPS receivers have been operated withas few as two satellites to provide a two dimensional position solutionusing both clock and altitude hold.

Because continuous reception from four GPS satellites is often difficultto maintain in a car navigation environment, and known clock andaltitude hold techniques can only permit operation with at least twosatellites, known conventional car navigation systems have typicallyaugmented the GPS position information with information from externalsensors to provide dead reckoning information. The dead reckoninginformation is often provided by an inertial navigation system such as agyroscope.

Augmenting GPS data with inertial navigation data has permitted the useof GPS car navigation even when less than 4 satellites are visible, suchas in tunnels and in urban situations between tall buildings. However,the resultant increased complexity and costs for such combined systemshave limited their acceptance.

Conventional GPS receivers use separate tracking channels for eachsatellite being tracked. Each tracking channel may be configured fromseparate hardware components, or by time division multiplexing of thehardware of a single tracking channel, for use with a plurality ofsatellites. In each tracking channel, the received signals areseparately Doppler shifted to compensate for the relative motion of eachsatellite and then correlated with a locally generated, satellitespecific code.

During a mode conventionally called satellite signal acquisition,delayed versions of the locally generated code for the satellite beingacquired are correlated with the Doppler rotated received signals tosynchronize the locally generated code with the code, as received forthat satellite, by determining which delay most accurately correlateswith the code being received. Once synchronization has been achieved fora particular satellite, that satellite channel progresses to a trackingmode in which the Doppler rotated, received signal is continuouslycorrelated with the locally generated code for that satellite todetermine position information including pseudorange information. Duringtracking, conventional receivers also correlate the Doppler shiftedreceived signal with one or more versions of the locally generated codeat different relative delays, such as one half C/A code chip width earlyand late relative to the synchronized or prompt version of the code.These early and late correlations are used to accurately maintain thesynchronization of prompt correlation.

When, after tracking has begun for a particular satellite, the satellitesignal has been lost so that the required timing of the locallygenerated code for synchronization is no longer accurately known,conventional receivers reenter the acquisition mode, or a limitedversion of this mode, to reacquire the satellite signals by multiplecorrelations to resynchronize the locally generated code with the codeas received. Once the locally generated code has been resynchronizedwith the signals as received, position information data is again derivedfrom the signals from that satellite.

GPS systems, as well as many other radio frequency (RF) communicationsystems utilizing frequencies high enough to be considered line of sightsystems in which there must be a substantially direct line of sightbetween the transmitter(s) and receivers(s) for optimum operation, oftensuffer from multipath effects in which the receiver(s) must processsignals received over a multiplicity of different paths. A commonexample is a simple broadcast TV system in which a TV receiver with anantenna receives multiple copies of the signal being transmitted.

The multiplicity of signals being received results from additional,typically unwanted, signals paths including one or more reflections.When the signal path from the transmitter to receiver includes areflection, this signal path must by definition be longer than thedirect path. Multipath signals present a problem in systems, such as GPSsystems, in which the time of arrival of the signal is to be measured orused because the time of arrival of the multipath signals depends on thelength of the path(s) taken.

The straightforward processing of all signals, including multipath orreflected signals, often degrades the processing performed by thereceiver. In the simple broadcast TV transmission system describedabove, the processing of unmodified multipath signals by the receiverresults in the commonly experienced degradation called “ghosting” inwhich multiple signals are displayed offset in the TV image. Themultiplicity of displayed offset video signals results from thedifference in path lengths of the various multipath signals received.

The direct path is the shortest and therefore requires the least traveltime from transmitter to receiver while the various unwanted multipathsignals have various greater lengths, and therefore various longertravel times, than the direct path signals. Signals are processed inpart in a TV receiver in accordance with their time of arrival andtherefore the resultant video display may include a plurality of imagesslightly displaced in space on the TV monitor in accordance with theirdifferent path lengths.

Many conventional partial solutions to the problems of multipathreception exist. In the TV broadcast example, a highly direction antennais often used for the receiver to reduce the number of multipath signalsprocessed by the receiver. In addition, various discriminationtechniques have been developed which use the knowledge that theamplitude of the direct path signal is typically substantially greaterthan that of the unwanted multipath signals because signal amplitude isdegraded by the square of the path length.

In other types of systems, such as the GPS systems using PRN encodedspread spectrum signals, certain conventional techniques are difficultor impossible to use. For example, GPS transmitters are positioned onsatellites with complex orbital paths so that the position of themultiple transmitters are constantly changing. This makes a highlydirectional antenna system almost completely unusable. Similarly,digital receivers, including those used in a GPS receiver, often do notrely solely on the amplitudes of the signals received, but rather relyon other signal characteristics, such as time of arrival.

Multipath processing techniques currently used for complex receivers,such as GPS receivers, are often quite complex and subject toinaccuracies. An example of one such conventional technique is describedin U.S. Pat. No. 5,414,729 issued on May 9, 1995 to Patrick Fenton andassigned as issued to NovAtel Communications Ltd., Canada. In thistechnique, an autocorrelation function of a partially processed receivedsignal, including multipath components, is compared to an estimatedautocorrelation function of an estimated direct path signal to attemptto discern direct path signals from multipath signals for furtherprocessing. This technique of comparing processed and estimatedcorrelation power, is complex and may be subject to error in that thepartially processed signals relied on are themselves subject todegradation from many effects in addition to multipath effects includingreceiver limitations, which may reduce the accuracy or effectiveness ofthe multipath processing techniques.

For example, in tracking a GPS C/A signal to determine positioninformation from GPS satellite transmitters, it is typically importantto derive an accurate estimate of the time of arrival, known as codephase, of the PRN modulation of the direct path component of the C/Asignals received from each of the various GPS satellites. It is alsoimportant to derive an accurate estimate of the phase of the underlyingcarrier signals transmitted from the satellites on which the modulationis applied, known as the carrier phase. However, as apparently shown forexample in FIGS. 6, 7 and 8 of the above referenced Fenton patent, thedelayed multipath components degrade the tracking of the code andcarrier phase estimates by distorting the correlation functions used issuch tracking.

What is needed is an improved spread spectrum receiver, such as one foruse with GPS navigation systems, which avoids the limitations ofconventional designs and provides improved results in a wide range ofreception conditions, including multipath interference.

SUMMARY OF THE INVENTION

In one aspect, the present invention provides an improved terrestrialnavigation system using a GPS receiver which can continue to navigatewith continuous GPS data from less than the 3 or 4 GPS satellitescommonly required. The GPS data is augmented with data from anothersource. The source of the augmentation data may include data fromexternal sensors, data bases including map data bases, and/or knowledgeof the physical environment within which the vehicle is to be navigated.The use of such augmentation data permits GPS satellite navigationsolutions for stand-alone GPS systems as well as for GPS systemsintegrated with external sensors and/or map databases with less than 3or 4 continuously visible GPS satellites.

In other aspect, the present invention provides a GPS system which usesa digital ASIC and RF chipset and a relatively wide IF band. A simple,2-pole LC IF filter is associated with the RF chip while a decimator ordigital filter associated with the digital chip to run the system at areduced clock rate. The simple 2-pole filter is used in lieu of the morecomplex and expensive 5 or 6 pole filter that would otherwise, be usedin a conventional receiver system of this type.

In another aspect, the present invention provides a GPS receiver inwhich map data used to determine routing is also used as a source ofdata augmentation for a single satellite solution by providing directionof travel information.

In still another aspect, the present invention provides a method ofaugmenting GPS data using information from the physical environment. Forexample, vehicles are usually constrained to tracks no wider than thewidth of the roadway—and often to tracks only half the width of theroadway—and trains are constrained to the width of their tracks. Thiscross track constraint data may be used to provide augmentation data andallow the vehicle to continue to navigate with only a single satellitein view. The cross track constraint data permits the computation ofalong track data useful for calculating total distance traveled toprovide a GPS based odometer measurement.

The present invention permits the computation of distance along trackfor use as an odometer reading while tracking only one satellite. Crosstrack hold provides along-track data directly which, in the case of avehicle, directly provides distance traveled information useful in lieuof a conventional odometer reading.

In addition to clock and altitude hold, the present invention uses atechnique which may be called cross-track hold in which the singlesatellite in view is used for determining the progress of a vehicle suchas a car along its predicted track, such as a roadway. The dataconventionally required from a second satellite is orthogonal to thetrack and therefor represents the appropriate width of the roadway. Thisvalue may be assumed and or constrained to a sufficiently small value topermit an estimate of the value, e.g. y_(est) to provide a modedescribed herein as cross-track hold while obtaining useful GPSnavigation from a single satellite in view.

In other words, in accordance with the present invention, singlesatellite navigation may be achieved by using the data from the singlesatellite for on-track navigation information while holding orestimating the time, altitude and/or cross-track navigation data.

The required augmentation data may additionally, or alternatively, bederived from other sources in the physical environment, such as turnsmade by the vehicle during on-track travel. In accordance with anotheraspect of the present invention, the vehicle may detect turns madeduring travel and update the current position of the vehicle at the turnin accordance with the timing of the turn. Turn detection may beaccomplished by monitoring changes in the vehicle vector velocityderived from changes in the GPS derived position information or bymonitoring changes in the compass heading or by any other convenientmeans.

In another aspect, the present invention provides a GPS system fornavigating a vehicle along a track, including means for tracking atleast one GPS satellite to provide on-track information related toprogress of the vehicle along a selected track, means for providing anestimate of cross track information related to motion of the vehicleperpendicular to the track, and means for providing vehicle navigationdata, such as vehicle position or vehicle velocity, from the on-trackinformation and the cross-track estimate.

In still another aspect, the present invention provides a method ofderiving position information from a single GPS satellite by tracking atleast one GPS satellite to provide on-track information related toprogress of the vehicle along a selected track, providing an estimate ofcross track information related to motion of the vehicle perpendicularto the track, and determining the position of the vehicle from theon-track and the cross-track estimates.

In still another aspect, the present invention provides a method ofupdating GPS position information for a vehicle navigating on roadwaysby deriving an indication that the vehicle has made a turn at aparticular point along a predetermined track, comparing the turnindication with stored navigation data to select data related to one ormore predicted turns at or near the particular point, comparing the turnindication with the predicted turn data to verify that the indicatedturn corresponds to the predicted turn, and updating GPS positioninformation to indicate that the vehicle was at the predicted turnlocation at a time corresponding to the turn indication.

In still another aspect, the present invention provides a GPS system fornavigating a vehicle, the system including means for tracking at leastone GPS satellite to provide on-track information related to thedirection of travel of the vehicle along a selected track, and means forderiving vehicle navigation data from changes in the direction of travelof the vehicle along the selected track.

In a still further aspect, the present invention takes advantage of thetypical improvement in satellite visibility possible in urban roadwayintersections by providing a fast satellite reacquisition scheme whichpermits data from otherwise obscured satellites to aid in the navigationsolution even though visible only for a short time, for example, as thevehicle crosses an intersection in an urban environment in which tallbuildings obscure the satellites from view except in the intersection.

In a further aspect, the present invention provides a spread spectrumreceiver having means for providing a plurality of versions of a locallygenerated signal related to a spread spectrum signal to be received,means for combining at least two of the versions of the locallygenerated signal with the spread spectrum signal to produce a productsignal related to each of the at least two versions, means forevaluating the at least two product signals to adjust a parameter of thethird version of the local signal, means for combining the adjustedthird version of the local signal with the spread spectrum signal toproduce a data signal, means for determining a predicted value of theparameter when the spread spectrum signal becomes unavailable, means forcombining an additional plurality of versions of the locally generatedsignal related to the predicted value with received signals to produceadditional product signals related to each of the additional pluralityof versions of the locally generated signal, means for evaluating theadditional product signals to produce a reacquired data signal.

In another aspect, the present invention provides a method of operatinga receiver for coded GPS signals from satellites by correlating early,prompt and late versions of a locally generated model of the code withsignals received from GPS satellites to adjust a delay of the promptversion to track a selected satellite, maintaining a predicted value ofthe delay when the selected satellite is unavailable, correlating aplurality of different early versions of the locally generated code withsignals received from satellites to produce correlation products,correlating a plurality of different late versions of the locallygenerated code with signals received from satellites to producecorrelation products, and reacquiring the previous unavailable selectedsatellite by selecting the version producing the largest correlationproduct above a predetermined threshold as a new prompt version of thecode to track the satellite.

In a still further aspect, the present invention provides a spreadspectrum receiver for a spectrum spreading code having a fixed number ofbits repeated during a fixed length time period from a plurality oftransmitters having a first time slicing level for slicing the timeperiod of the transmitted code into a number of time segments evenlydivisible into the twice the number of samples, a second multiplexinglevel for dividing each time segment into a number of channels, each ofthe channels being used for tracking one of the transmitters, and athird level dividing each of the channels in one of the segments into anumber of code phase delay tests.

In another aspect, the present invention provides a receiver forprocessing signals from a plurality of sources, each modulated by adifferent spectrum spreading code repeating at a common fixed interval,including a sampler for deriving digitally filtered I and Q samples froma composite of spread spectrum signals received from the plurality ofsources, means for segregating samples of the signals being receivedduring each interval into a number of time segments, a time divisionmultiplexer for segregating different versions of the sequential samplesinto each of a number of channels, each channel representing one of theplurality of sources, a correlator for correlating the version of thesample in each channel with a series of sequentially delayed versions ofthe spectrum spreading code applied to the signals from the sourcerepresented by that channel, and an accumulator associated with each ofthe series of delays in each of the channels for processing the resultsof correlations performed during one or more intervals to deriveinformation related to the signals.

In another aspect, the present invention provides a GPS receiver inwhich the residual code phase tracking, or pseudorange, error due tosimultaneous reception of multipath signals is detected, estimated andcorrected. In particular, the distortion of the correlation function ofthe multi- and direct path signal composite as received with theinternally generated code is detected by comparison of an aspect ofresultant correlation function with a model of the correlation functionexpected in the absence of multipath distortion. The comparison providesan indication of the sign of the residual error.

It has been determined that the composite of a direct path and one ormore multipath signals distorts the correlation function. If, as in mostcommon cases, the multipath signal(s) are weaker than the direct pathsignals, the interference between such signals as received results in apredictable distortion of the correlation function. If the carrierphase(s) of the multipath signal(s) are shifted from between about 0° to90° from the carrier phase of the direct path signal, the signals tendto reinforce each other resulting in a widening of the correlationfunction. Similarly, if the carrier phase(s) of the multipath signal(s)are shifted from between 90° to about 180° from the carrier phase of thedirect path signal, the signals tend to cancel each other resulting in anarrowing of the correlation function.

The correlation products are used in a code tracking loop to track anddetermine code phase. The most common scheme is to track points of equalmagnitude (or power) separated by one C/A code chip width and estimatethe time of arrival of the direct path signal as the mid-point betweenthese points of equal magnitude. The points of equal magnitude on eitherside of the direct path arrival time are known as the early and latecorrelation time and the estimated arrival time of the direct path iscalled the punctual correlation time. In the presence of multipathsignals, the correlation function has been found to be distorted so thatthe mid-point between the early and late correlations, that is theprompt correlation, is not an accurate estimation of the arrival time ofthe direct path signal.

When the correlation function of the composite is distorted to be widerthan the correlation function expected for a direct path only signal,the distortion results in a lag error in which the prompt correlationlags the actual direct path signal received. Similarly, when thecorrelation function of the composite is narrower than expected, thedistortion results in a lead error in which the prompt correlation leadsthe time of arrival of the direct path signal.

The prompt correlation therefore leads or lags the actual time ofarrival of the direct path signal by an amount designated herein as theresidual code tracking error. The magnitude of the error can beapproximated by the degree of narrowing or widening of the correlationfunction. Reduction of this error, or detection and correction of theerror, enhances the accuracy of the resultant position determination.

The present invention also provides an improved multipath signalprocessing technique which directly cancels the effect of multipathsignals by processing the composite of direct and multipath signals asreceived to create a synthesized replica of the signal as received whichmay then be subtracted from the signals as received to cancel oreliminate the effects of the non-direct path, unwanted multipathsignals. As a result of the steps required to create a replica whichwill actually cancel the signal as received, the actual carrier and codephases are accurately determined without degradation by multipathcomponents. The cancellation may preferably occur after the receivedsignals have been partially processed to reduce complexity of the systemand required signal processing and enhance accuracy of furtherprocessing.

In another aspect, the present invention provides an improved techniquefor multipath signal processing in which a tracking loop applied to thesignal as received is used to synthesize an accurate replica of thesignals as received, including multipath components. The replica is thencanceled from the signal being processed to decode the signal asreceived without multipath degradation. The replica signal issynthesized to approximate, using least squares or similar approximationtechniques, the GPS signal as received including distortions caused bymultipath. This provides a useful estimate of the multipath signalprofile. From this estimate, relatively accurate measurements of codeand carrier phase of the direct path GPS signal received are derived.

In still another aspect, the present invention provides a spreadspectrum receiver including a multi-bit digital correlator forcorrelating each sequential segment of a spread spectrum signal with atleast one series of differently time delayed code replicas and matrixmeans responsive to the correlator to derive code source specificinformation. The multibit correlator may be configured from a set ofcorrelators for simultaneously correlating portions of each sequentialsegment with portions of a segment of a code replica. The series ofdifferently time delayed code replicas may be sequential or interlaced.

For efficient C/A GPS operation, each segment should include a signalsample having a duration of an integral number of half chip widthsproportional to a number selected from 3, 11 and 31 while the number ofsatellite channels and time delays are proportional to the others ofthose numbers. The multi-bit correlator operates upon a first sequentialsegment while the sample register collects a subsequent sequentialsegment. The matrix means includes m times n data cells for storing datarelated to the correlation of the spread spectrum signal and thereceiver may be selectively operated to form either n different codespecific sets of m different time delayed correlation products or ntimes m different time delayed correlation products for one code.

The series of time delayed code replicas covers a tracking window oftime sufficient to track a prompt time delay from a selected codetransmitter as well as additional time delayed code replicas covering arecapture window of time separate from the tracking window. Therecapture window is sufficiently large to include a prompt time delaycorrelation product for each code after predictable periods of codetransmitter obscuration during normal operation of the receiver.

Multipath performance is improved by use of tracking means responsive tothe matrix means for tracking a prompt delay from a source of the codetogether with means for monitoring correlation products representinglesser time delays than the prompt delay to detect the inaccuratetracking of a multipath signal from the source of the code. In addition,multipath errors are reduced by analyzing the ratios of correlationproducts surrounding the prompt correlation to correct for interferenceusing means for causing correlation products of two of the time delayedreplicas to be equal together with means for selecting the prompt delayin response to the ratio of the amplitude of the equal correlationproducts to a correlation product having a time delay therebetween. Theprompt time delay is selected to be less than half way between the timedelays of the equal correlation products if the ratio of the amplitudesof the equal correlation products to a correlation product having a timedelay half way between the time delays of the equal correlation productsis greater than one or more than half way between the time delays of theequal correlation products if the ratio of the amplitudes of the equalcorrelation products to a correlation product having a time delay halfway between the time delays of the equal correlation products is lessthan one.

IF bandwidth improvement is provided by use of sampling means forforming digitized samples of signals received from code sources at afirst rate and digital filtering means for forming the sequentialsegments from the digitized samples at a second rate substantiallyslower than the first rate.

Hand held operation is aided by use of means for temporarilyinterrupting correlation for multiple code periods to reduce receiverenergy consumption and means for resuming correlation to continuederiving code source specific information. The correlation may beresumed periodically to provide an apparently continuous display. Theperiods of interruption are a multiple of the code period and shortenough so that unmodeled clock drift is less than the difference in timebetween the time delays used for the correlation of signals from a codesource. Correlation may also be resumed in response to means formodeling clock drift for synchronizing a local clock with a clockassociated with a single source of the code or in response to operatorinteraction.

In a still further aspect, the present invention provides a method ofoperating a GPS C/A code receiver by forming x multibit digital segmentvalues per C/A code period, each representing a sequential segment of areceived composite of satellite signals, correlating each digitalsegment value with n satellite specific sets of m differently timedelayed segments of C/A code modulation to form at least n times m timedelay specific correlation values, and determining navigationinformation from the correlation values, where x, m and n are each primefactors of the number code chips per C/A code period.

Multipath performance is improved by comparing the magnitudes of twoequal correlation values to the magnitude of a correlation valuetherebetween to select a prompt delay more than half way between thetime delays represented by the equal correlation values when themagnitude of the equal correlation products is equal to less than halfof a peak correlation value therebetween or less than half way betweenthe time delays represented by the equal correlation values when themagnitude of the equal correlation products is equal to more than halfof a peak correlation value therebetween.

Battery operation is improved by interrupting the step of correlatingfor a series of code periods to reduce receiver energy consumption. Theinterruption period is less than the time required for an internalreceiver clock to drift the time delay represented by the series of timedelay segments related to one particular satellite. Correlation isresumed periodically to update the display or to update the internalclock or in response to operator intervention in a push-to-fix mode.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is an overview illustration of the operation of a car navigationsystem according to the present invention.

FIG. 2 is a block diagram of the GPS car navigation system depicted inFIG. 1, used for improved navigation during reduced satellitevisibility.

FIG. 3 is a schematic representation of a single satellite channel of aGPS receiver used for fast satellite reacquisition.

FIG. 4 is a schematic representation of a portion of the singlesatellite channel shown in FIG. 3 in which an additional plurality ofsets of delayed code samples are correlated to provide a finer gradationof correlation intervals.

FIG. 5 is a functional block diagram of a preferred implementation, onan ASIC, of the satellite tracking channels and associated processingcomponents of the GPS car navigation system shown in FIG. 1.

FIG. 6 is a functional block diagram of the Doppler Block of the GPS carnavigation system shown in FIG. 1.

FIG. 7 is a functional block diagram of the Coder Block of the GPS carnavigation system shown in FIG. 1.

FIG. 8 is a functional block diagram of the Correlator Block of the GPScar navigation system shown in FIG. 1.

FIG. 9 is a function block diagram overview showing the interconnectionsbetween the Doppler, Code, Correlator and other blocks of the systemdescribed in FIG. 5.

FIG. 10 is a block diagram of the operation of the system, shown inFIGS. 5 and 9, illustrating the data path of the present invention.

FIG. 11 is a series of exploded time segments illustrating the operationof the data path of the present invention.

FIG. 12 is a block diagram overview of a GPS receiver systemillustrating a complete receiver system according to the presentinvention including a more detailed view of the satellite receiversection shown in FIG. 2.

FIG. 13 is a block diagram description of GRF1 204.

FIG. 14 is a pin out of GRF1 204.

FIG. 15 is a timing diagram of the AGC interface.

FIG. 16 is an connection diagram showing a preferred interconnectionbetween ASIC GSP1 202, GRF1 204 and the related components.

FIG. 17 is a graph of the correlation product of a direct path signalreceived without multipath interference, together with correlationproducts distorted by the presence of multi-path signals whose carrierphase differs from the carrier phase of the direct path signal by about0° and by about 180°.

FIG. 18 is a schematic block diagram of portions of a GPS receiverillustrating the delay-locked tracking loop with multipath residual codephase error detection, calculation and/or correction according to thepresent invention.

FIG. 19 is a block diagram schematic of a portion of a GPS receivershowing another embodiment of the present invention in which multipathsignal replicas are produced in an error tracking loop for latercancellation in a carrier tracking loop.

FIG. 20 is a block diagram schematic of a portion of a GPS receivershowing still another embodiment of the present invention in whichparallel processing paths are used to track predicted values of anunknown Nav Data Modulation bit until the bit is demodulated forcomparison and selection.

FIG. 21 is a block diagram schematic of a system similar to that shownin FIG. 20 in which the predicted Nav Data Bit Modulation is strippedfrom the raw signals to be processed rather than being added to the codephase applied to the error tracking loops.

FIG. 22 is a schematic representation of the matrix of accumulatedcorrelation products for several SVs at several times showing theplacement of the early, prompt and late correlation products for thedirect and multipath signals at various location within the 22 tap delayline illustrating code phase verification and direct and multipathsignal modeling.

FIG. 23 is a schematic representation of the operation of one embodimentof the system according to the present invention in which a separatechannel is used in a fast acquisition mode for code phase verificationfor all SVs sequentially.

FIG. 24 is a block diagram of an alternate embodiment of the GPS carnavigation system depicted in FIG. 2 used for improved navigation duringreduced satellite visibility.

FIGS. 25A and 25B are diagrams illustrating cross track error resultingfrom the use of a straightline predicted track.

FIG. 26 is a flow chart diagram of an energy reducing sleep mode ofoperation in accordance with the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

FIG. 1 is an overview illustration of the operation of a GPS carnavigation system according to the present invention. The GPS carnavigation system, described below in greater detail with respect toFIG. 2, is mounted in car 10 which is moving along the center of roadway12. NAVSTAR satellite 14, in the lower left quadrant of the figure, isin view of car 10. A simulated GPS circular overhead display, positionedapproximately over intersection 22 of roadway 12 and roadway 16indicates that satellite 14 is between 0° and 45° degrees of elevationabove the horizon as viewed from car 10.

For the purposes of illustration, satellite 18 is positioned overheadbetween the elevation angles of 0° and 45° degrees. However, the line ofsight between satellite 18 and car 10 is obscured by buildings 20 sothat satellite 18 is not in view of car 10 at the position along roadway12 as shown. Similarly, the line of sight between satellite 19 and car10 is obscured by buildings 21. However, as will be discussed below,when car 10 crosses intersection 22, the line of sight between satellite19 and car 10, when the car is in position 11 within intersection 22,may momentarily be clear.

Turning now to FIG. 2, GPS car navigation system 24 is a firstembodiment of a car navigation system according to the present inventionwhich may be installed in car 10 of FIG. 1. GPS car navigation system 24includes GPS car system module 26 which is provided with signalsreceived from satellites by GPS antenna 28, data related to the thencurrent—and expected future—physical environment of car 10 by forexample map data base 30 and data input from the operator of the car byfor example input device 32. GPS car system module 26 provides output tothe operator, for example, in the form of a GPS map display, via displayunit 34, which may include both visual display as well as a voiceinterface announcing information as required to supplement or evenpartially replace visually presented data.

The present invention may be configured for use with only a GPSreceiver, a GPS receiver aided by map data from, for example, map database 30, and/or a GPS receiver aided by both a map data base as well asan external source of information, for example, from an external sensor.This external source of information may be used for maintaining positioninformation by dead reckoning during those times when a sufficientnumber of satellites are not in view to provide the desired information.

In operation, a composite of all signals received from NAVSTARsatellites is applied by GPS antenna 28 to satellite receiver section 36of GPS car system module 26. Signals from individual NAVSTAR satellitesare then tracked in satellite specific tracking channels such as SatTRAKchannels 38, 40, 42 and 44. Although it is quite conventional to track 4to 12 satellites and therefore use 1 to 12 satellite tracking channels,only 4 such channels are shown herein for clarity. The outputs of thesesatellite specific tracking channels are processed by SatProcessor 46 toprovide x_(user), y_(user), z_(user) and t_(user) data via appropriatelogic control to a GPS position processor, such as PosProcessor or NavSoln 48 which determines the navigation solution to determine positiondata. Position data is then applied by PosProcessor 48 to an appropriatedisplay for the operator of the car, such as display unit 34.

External sensor 49, in FIG. 2, may conveniently provide sensor data, orlocal or satellite position information, or position information whichprovided local position or satellite position information directly toPosProcessor 48 for comparison with the position information determinedby SatProcessor 46 and/or Map/Display Processor 50. External sensor 49may conveniently be any sensor which provides information useful forupdating position information for dead reckoning including direction,speed, velocity or acceleration or other data from which dead reckoningdata may be derived. Conventional sensors include inertial navigationsystems, with magnetic or optical gyroscopes, fluxgate compasses,odometer or wheel sensors or the like. Alternatively, external GPSformat signals, such as those provided by a pseudolite, may be used toupdate current satellite or position information.

At the beginning of a navigated trip, the operator of car 10 wouldtypically provide data concerning the physical environment surroundingthe intended route to GPS car system module 26 by inserting anappropriate data storage device such as a CD ROM, into map data base 30,and/or by entering the data via input device 32 which conveniently maybe a keypad, keyboard, pointing device, track ball, touch screen,graphical pad, a voice recognition interface and/or a combination ofsuch input devices. The operator of car 10 would also enter the intendeddestination into GPS car system module 26 via a data entry device suchas a mouse or track ball interacting with display unit 34 and/or viainput device 32. Map/Display Processor 50 of GPS car system module 26would then develop the desired route, typically from the then currentlocation as a point of origin to the desired destination, in accordancewith the rules of navigation and details of the locale provided by mapdata base 30. The appropriate route data is stored in Route Data Base52, including the routing in the form of roadways and turns betweenroadways. Additional information, such as altitude, width of theroadways and etc. may also be contained within map data base 30 and/orRoute Data Base 52. These data bases may be contained within GPS carnavigation system 24 and/or be made available to GPS car system module26 from outside storage media such as diskettes positioned inappropriate disk drives.

During navigation, each satellite in view may be tracked in a satellitetracking channel. If, for example, 4 or more satellites are in view,each of the satellites in view will be tracked in an individual channel,such as SatTRAK channels 38, 40, 42 and 44. The output of the satellitetracking channels is then applied to SatProcessor 46 which would providesatellite based solutions of the four unknowns, such as x_(user),y_(user), z_(user) and t_(user). The data represented by x_(user) andy_(user) are conventionally used as the two dimensional orthogonalcomponents of the surface of the earth such as north and east. However,in accordance with the present invention, x_(user) and y_(user) arepreferably used to represent data for a pair of orthogonal directionsspecific to the direction of vehicle travel called the on-track andcross-track directions.

Conventional bearing, such as north, south, east and west are relativeto the magnetic or true north poles of the earth, while on-track andcross-track, as used in the present invention, are bearings maderelative to the expected direction of travel of car 10 at any particularpoint in the route. For example, while a 90° turn from a heading of duenorth would change the angle of the vehicle velocity vector from 0° to90° if bearings relative to the Earth's surface such as north and eastare used, the same turn would show no change in the 0° angle of thevehicle velocity vector before or after the turn as long as car 10remained on the expected track.

The data represented by z_(user) is typically surface elevation, such asthe elevation above sea level, while the data represented by t_(user) isthe exact time as determined from one or more of the satellite trackingchannels.

Solutions for all 4 unknowns of position information may be derived fromsignals from 4 satellites in view, so that exact position informationwithin the limit of the accuracy then available from the GPS satelliteconstellation in view can therefore be applied by PosProcessor 48 toMap/Display Processor 50. The position information determined from thesatellites is processed with the physical data from map data base 30,and/or the desired routing data from Route Data Base 52, to provideappropriate navigation information to the operator of car 10 via displayunit 34.

If less than 4 satellites are in view, the t_(user) solution applied toPosProcessor 48 may be replaced by t_(est) 54 estimated solution derivedfor example from an internal clock model 54 in position estimate ormodel 63. Similarly, the z_(user) solution may be replaced by z_(est) 56solution derived from elevation estimate 56, also in position model 63,in accordance with routing data derived from Route Data Base 52 inaccordance with then current GPS position information applied toMap/Display Processor 50. T_(est) 54 and z_(est) 56 are applied toPosProcessor 48, and used in lieu of t_(user) and z_(user), when onlytwo satellites are in view. The use of estimated or modeled solutionsfor the t and z variables, that is the use of t_(est) 54 and z_(est) 56are conventionally known as clock hold and altitude hold, respectively.

It must be noted that the particular configuration of GPS car navigationsystem 24 as described so far is only one of the many known ways ofconfiguring such systems any of which may be used without departing fromthe spirit or scope of the present invention as defined by the claims.

In accordance with the present invention, the width of the roadway,either known or estimated, may be used to provide y_(est) 60 for use inlieu of y_(user) when only one satellite is visible. y_(est) 60 may bederived from Route Data Base 52 and/or map data base 30. Since the x andy unknowns are orthogonal, x_(user) may be used to describe the on-trackinformation, that is, the progress of car 10 along its predeterminedtrack while y_(est) 60 represents the cross track information, that is,how far car 10 has strayed from the center of the roadway.

Referring therefore to FIG. 1, x_(user) is used to indicate the progressof car 10 along roadway 12 while y_(est) 60 is used to represent thewidth of roadway 12. The actual width of the roadway may be derived frommap data base 30, or assumed because the actual value of the width ofthe roadway is relatively small and often therefore insignificantcompared to the distances to be measured along the navigation route.Since the maximum allowable cross-track error, i.e. the maximumallowable appropriate value for y, is constrained by the physical widthof the roadway, y_(est) 60 is relatively easy to accurately estimate.

By using y_(est) 60, z_(est) 56 and t_(est) 54, it is possible toprovide useful navigation data for car 10 along a known roadway usingsignals from only a single satellite in view. It is important to notethat reasonably accurate prior or initial position information may berequired and that not all visible NAVSTAR satellites will be suitablefor single satellite navigation, depending upon the position of thesatellite with respect to the path of car 10. The position informationdetermined during single satellite navigation is along track positioninformation which may be accumulated and used for determiningaccumulated along track distance traveled. This data provides, and maybe used in place of, the distance traveled information conventionallyprovided in a vehicle by an odometer.

Referring now to both FIGS. 1 and 2, turning data may be used to improveterrestrial GPS navigation by using the detection of a known turn toupdate progress along a predetermined route. When at least 4 satellitesare in view, the position of car 10 may be known to the accuracy of theGPS system. When using clock, altitude or cross-track hold, or somecombination thereof, the known position of the car is degraded by anyinaccuracy of the estimate or estimates used. For example, during clockhold, internal clock model 54 drift and inaccuracy of the source oft_(est) 54 will degrade the accuracy to which the position is known as afunction of the magnitude of the inaccuracy. Similarly, any change inaltitude from the estimated or fixed altitude, that is, any inaccuracyof z_(est) 56, will degrade the accuracy of the known position. Changesin roadway width and inaccuracies in the map data with regard to theroadway width, that is, any inaccuracy in y_(est) 60, may also degradethe position information.

Even with 4 satellites in view, the geometry of the visible satellitesmay make it difficult to determine position by measurement of GPSsignals. Further, during terrestrial navigation, it is not uncommon forsatellites to be temporarily obscured from view during navigation by,for example, being blocked by buildings and other obstructions.

It may therefor be desirable to update the accuracy with which thecurrent position of the vehicle is known with actual positioninformation whenever possible. The update information will sometimes beuseful when 4 satellites are in view, but will always be useful assupplemental data when less than 4 satellites are in view. Updateinformation is extremely useful during single satellite navigation toavoid the accumulation of errors in position information.

In operation, an original position and a destination were provided tothe system which then determined the track to be followed. The track tobe followed, or routing information, may be provided in the form of adata base of route information such as Route Data Base 52. In theexample used, track 62 follows the centerline of roadway 12 tointersection 22 and then makes turn 64 to follow the centerline ofroadway 16. Track 62, roadways 12 and 16, intersection 22 and turn 64are provided to Route Data Base 52 during the preparation of the routeby Map/Display Processor 50 from the then current position and thedestination entered via input device 32.

The physical position of car 10 is very accurately known when car 10turns at turn 64. This accurate knowledge of the car's position at aparticular time may conveniently be used to update the GPS navigationinformation by providing a position reset which is similar to a knowninitial position. Update information from turns will most likely beuseful if the angle of turn 64 is sufficiently large to provide anunambiguous position determination. It is expected that any turn greaterthan 45° may be detected. As the speed of the vehicle increases, smallerturn angles may also provide useful information. The position updateinformation is applied to position model 63 to update internal clock ort_(est) model 54, elevation or z_(est) model 56, y_(est) model 60 aswell as x_(est) 61 which is a model of the along-track position of thecar. These four estimates together for position model 63, which may beupdated by information from map data base 30, Route Data Base 52,current position processor 70, PosProcessor 48 and/or external sensor49, to form the most accurate available position model 63. Positionmodel 63 may also be used to provide estimates to the same data sources.

The actual turning of the car may be detected by a change in the vehiclevelocity vector determined from the GPS data or from other conventionalmeans such as a magnetic compass or an inertial navigation sensor. Inaccordance with the rapid reacquisition system described below withrespect to FIG. 3, GPS data alone may conveniently detect such turnseven when single satellite navigation is required. The turn as detectedby turn detector 66 is correlated with data from Route Data Base 52 todetermine the actual position of the car to the accuracy of the map database 30. The accuracy of the data in map data base 30 may easily andconveniently be much greater than the accuracy available from the GPSsystem especially if single satellite navigation, or any combination ofclock, altitude or cross-track hold, is used. Therefore the positionupdate may provide a substantial increase in the accuracy of the thencurrent position determination.

The benefit of the approach of this embodiment of the present inventionis similar to the identification and use of a known waypoint during adead reckoning navigation run. The cumulative error is reducedsubstantially at the known waypoint so that additional, future positiondetermination errors do not carry the burden of an accumulation of pasterrors.

As shown in FIG. 2, Route Data Base 52 provides data related to track62, typically from Map Data Base 30, to Map/Display Processor 50 todisplay the current GPS position and may also provide similarinformation to turn detector 66, turn comparator 68 and/or currentposition processor 70 in order to update PosProcessor 48 with a positionreset.

Turn detector 66 may be configured in many different ways and is used todetect turns actually made by car 10 and select turns, such as turn 64,from Route Data Base 52 for later comparison with the detected turn. Inaccordance with a preferred embodiment of the present invention, turndetector 66 may operate on the current GPS position provided byPosProcessor 48 to develop a vehicle velocity vector position indicatingboth the direction and speed of travel. Substantial changes in thedirection portion of the vehicle velocity vector would indicate a changein direction, such as a turn. Turn detector 66 may therefore detectturns directly from the GPS information by determining the vehiclevelocity vector and detecting changes in the vehicle velocity vectorwhich represent a turn.

Turn detector 66, or another unit if convenient, also operates on theroute information provided by Route Data Base 52 to determine theexpected position of car 10 along track 62 based on the then current GPSposition information. Once the expected location of car 10 along theroute is determined, one or more turns in the area of the expectedposition of car 10 can be selected for comparison with the indicationsof a physical turn derived from the GPS data.

When changes in the actual vehicle velocity vector, as derived forexample from the GPS position data, compare appropriately with thechanges predicted at a particular turn as derived from Route Data Base52, the actual position of car 10 at the time of the turn can be veryaccurately determined and used to update the GPS data at the turn. Forexample, if an actual turn is detected from a change in the vehiclevelocity vector from the GPS position of car 10 near the time predictedfor that turn, the actual position of car 10 at the time of the turn canbe determined and used to update the then current GPS position for useas a position reset applied to PosProcessor 48.

Alternatively, turn detector 66 may use non GPS measurements fordetermining the occurrence of an actual turn of car 10, such as compassheadings or inertial navigation determinations derived for example fromexternal sensor 49, and applied directly to turn detector 66 or viaPosProcessor 48 as shown in FIG. 2.

Detection of turns from GPS signals may easily be accomplished as longas 2 satellites are in view and provide appropriate geometries fordetermining two dimensional coordinates of the car's position. Duringsingle satellite navigation, as described above, the use of turninformation for updating the last known position information becomeseven more important, but the location of the single satellite in view,relative to track 62, becomes of even greater importance so that actualturns may be accurately detected.

Turn detection may also be provided by monitoring changes betweenacquired and obscured satellites. If, for example, only satellite 14 wasvisible to car 10 on roadway 12 before intersection 22, and uponentering intersection 22, satellite 19 suddenly became visible whilesatellite 14 was momentarily obscured, the change over from satellite 14to satellite 19 could be used to indicate a turn in accordance with thedata from each satellite. Using a rapid reacquisition scheme, asdescribed herein below, the actual position at which the change ofdirection, that is, the position at which the switch between satellitesoccurs, can be sufficiently accurately determined to permit preciseposition update information at the turn.

Similarly, turn comparator 68 may conveniently be implemented withinAnother component of the system, such as PosProcessor 48, Map/DisplayProcessor 50 and/or SatProcessor 46, so that a candidate turn may beselected from the route data for track 62 for comparison with thedetected turn data.

Referring now to FIG. 3, in another embodiment, the present inventionprovides for fast reacquisition of satellite signals, useful for examplewhen a previously acquired satellite is obscured and then appearsperhaps for only a short time, for example, as a car travels through anintersection.

Referring to the line of sight between car 10 and satellite 19 as shownin FIG. 1, it is common in an urban environment for the buildings alongthe sides of the street to act as a barrier wall obscuring the lines ofsight to many GPS satellites. However, the barrier wall formed bybuildings 20 and 21 is commonly breached at intersections such asintersection 22. For example, car 10 while traversing intersection 22may reach position 11 in which the previously obscured line of sight toa satellite, such as satellite 19, is momentarily not obscured becauseof the break between buildings 20 and 21 at intersection 22. Thismomentary visibility of a previously obscured satellite may occur whilecar 10 is in the intersection or at the edges of the intersection.

The length of the momentary contact with satellite 19 is relativelyshort. For example, if intersection 22 is 60 feet wide and car 10 istraveling at 30 mph, the time taken to cross the intersection may be asshort as 1.3 seconds. Conventional GPS navigation systems would notreacquire and derive useful data from satellite 19, even if previouslyacquired, during this short time interval.

In accordance with another embodiment, the present invention makesmaximum use of such reacquisition opportunities by minimizing the timerequired for reacquisition, the collection of data and processing of thecollected data for position determination. Referring now to FIG. 3, aportion of SatTRAK channel 38 is shown in greater detail as an exampleof the configuration of each of the satellite tracking channels. Afteroriginal acquisition, SatTRAK channel 38 tracks a single satellite byoperating on satellite signals 72 received by GPS antenna 28. Satellitesignals 72 include the signals from the satellite being tracked bySatTRAK channel 38 and are demodulated and selected by being multiplied,in one of the correlators 74, by a copy of the 1023 chip pseudorandom,spread spectrum code applied to satellite signals 72 by the GPSsatellite. Correlators 74 may be configured from exclusive OR NOR gatesto minimize the time required for providing a correlation result.

During tracking, the copy of the code produced by code generator 76 andapplied to exclusive OR correlators 74 by delay 78 is synchronized withthe code in satellite signals 72, as received, so that the copy of thecode correlates with satellite signals 72. This may be accomplished inseveral different manners known in the art, including by shifting thetime of generation of the code in code generator 76 and/or adjusting theamount of delay applied by an external delay. In any event, the codeapplied to exclusive OR correlators 74 when SatTRAK channel 38 is lockedto the selected satellite, is synchronized with the code being receivedfrom that selected satellite. This correlation is commonly called theon-time or prompt correlation to indicate this synchronization.

Conventional GPS receivers maintain a lock on a satellite signal afteracquisition by performing additional correlations, often called earlyand late correlations or correlations performed by early and latecorrelators. These correlations are displaced in time by a certain delaysuch as one half the width of a C/A code chip from the on-time or promptcorrelator. That is, if the time of occurrence of a particular chip inthe satellite signals is time t0, the prompt correlator under idealconditions would multiply satellite signals 72 with a replica of thecode with the same chip at time t0. The early correlation would beperformed at time t0−½ chip and the late correlation would be performedat a time equal to t0+½ chip. Whenever the synchronization between codegenerator 76 and satellite signals 72 as received begins to drift, thecorrelation results begin to change in favor of either the early or latecorrelation at the expense of the prompt correlation.

One conventional approach to maintaining lock on the signals from aparticular satellite is to adjust the timing of code generator 76 with afeed back loop used to maintain the power in the correlation products inthe early and late correlators to be equal. In this way, code generator76 may be continuously resynchronized with satellite signals 72 so thatthe accuracy of the system is within one half chip in either direction(early or late) of the signals received.

When satellite signals 72 are temporarily lost, for example, because thesatellite signals are temporarily obscured by buildings 20 and 21 asshown in FIG. 1, various techniques are used to attempt to synchronizecode generator 76 with satellite signals 72 as received so that SatTRAKchannel 38 can reacquire the signals from-the desired satellite. Asnoted above, conventional techniques include clock and altitude hold andone embodiment of the present invention provides another techniquecalled cross-track hold.

However, unless the obscuration of the satellite signals is very brief,the accuracy of prediction of such techniques is not enough to maintainsynchronization exception for a very brief period of obscuration.

In accordance with another embodiment of the present invention,massively parallel correlation is used to create an expanded capturewindow of correlation capture around the then current predictedsynchronization time in order to immediately reacquire a previouslyacquired, and then obscured, satellite signal. In particular, the speedof reacquisition is made sufficiently fast according to the presentinvention so that useful GPS position data may be acquired during thetime car 10 travels through intersection 22 even though, for example,the signals from satellite 19 were obscured by buildings 20 until car 10was within intersection 22.

To this end, an expanded series of correlations are performed with aseries of delays a fixed fraction of a chip width, such as ½ chip width,apart extending both early and late of the predicted prompt correlation.As shown in FIG. 3, satellite signals 72 are devolved into a fixednumber of samples, by for example analog to digital conversion in A/DConverter 73, to provide n Signal Samples 75. A similar number of codesamples are provided through k fixed ½ chip width delays 78 to providek-1 sets of n Code Samples 80, progressing from a first set of n CodeSamples 80 with no delay to the k-1st set of n Code Samples 80 whichhave been delayed by a total of k delays 78. It is convenient to use ½chip delays for each delay 78, but other fractions of a chip width maybe used.

The {fraction (k/2)}th set of n Code Samples 80, or the set nearest{fraction (k/2,)} may conveniently be delayed the correct amount toperform the prompt correlation in one of the exclusive OR correlators 74with n Signal Samples 75 from A/D Converter 73 during tracking. The{fraction (k/2)}th −1 set of n Code Samples 80 may then be used toperform the early correlation while the {fraction (k/2)}th +1 set of nCode Samples 80 may then be used to perform the late correlation whiletracking. The additional correlations may also be performed duringtracking, but provide a substantial advantage when used duringreacquisition.

That is, in the present invention, the early, prompt and latecorrelations conventionally used in tracking may also be used duringreacquisition mode, aided by a substantial number of correlations usingadditional delays. Whether or not the early and late correlations areused, a convenient number of additional delays on each side of theprompt delay results from (k-1)=20 so that nine or ten ½ chip delays areprovided on each side of the {fraction (k/2)}th prompt delay. In thisway, correlations are performed during reacquisition at time delays of 5chip widths on either side of the predicted prompt or on-time delay.This represents an expanded capture window of on the order of ±5×300meters of potential error. That is, if the predicted synchronizationwith satellite signals 72 modeled by GPS car system module 26 drifted byas much as the equivalent of a ±1500 meter position error during signalloss from a particular satellite resulting from, for example obscurationin an urban setting, at least one of the plurality of exclusive ORcorrelators 74 would provide the required prompt correlation toimmediately lock onto satellite signals 72.

Once the correlations are performed, the correlation results for eachset of n Code Samples 80 are summed in summers 84 to produce a series ofvalues each separately indicating the correlation of n Signal Samples 75with each of the sets of n Code Samples 80. These correlation resultsare applied to threshold test 82, the output of which is applied toSatProcessor 46 only when satellite signals 72 have been successfullyreceived. The output of threshold test 82 specifies the number of delayswhich represent the prompt correlation for the reacquired satellitesignal. It is important to note that in accordance with the presentinvention, the satellite tracking and reacquisition modes are notseparated functions but rather interact seamlessly. That is, byproviding a substantially expanded capture window, the correlations usedfor tracking are also automatically useful for immediate reacquisitionas long the capture window is sufficiently wide to include any positionerror accumulated during signal obscuration or other loss.

Because the speed of reacquisition is very important in order tomaximize the opportunity to utilize the brief time during travel throughintersection 22 when satellite 19 may temporarily be in view, it isadvantageous to perform all such correlations in parallel. Further, itis advantageous to continuously perform all such correlations in thecapture window in order to minimize time when a satellite signal is notbeing tracked. In accordance with the presently preferred embodiment,exclusive OR correlators 74 are implemented in hardware rather thansoftware to maximize the speed of correlation and minimize any erroraccumulation by minimizing the time for reacquisition.

In operation, when car 10 follows track 62 along roadway 12, during atleast part of the time buildings 21 obscure the line of sight betweencar 10 and satellite 19. If satellite 19 had previously been acquired byGPS car system module 26, an approximate time value to synchronize withthe satellite signals will be predicted. This value is maintained asaccurately as possible within GPS car system module 26 while satellite19 is obscured. In order to maintain the prediction for the requireddelay as accurately as possible, that is, to minimize the position erroraccumulated during signal loss, the above described techniques formaintaining or updating position accuracy by using cross-track hold,resetting position at a determined turn and/or the use of externalsensors for dead reckoning provide a substantial benefit for use withthe combined, expanded tracking and reacquisition windows describedabove.

Present technology makes it convenient to provide ½ chip delays betweencorrelators, but other delay values may be used. Similarly, it isconvenient to expect that the prompt correlation can be maintainedwithin plus or minus 5 chips of the timing of the satellite signals.FIG. 3 therefore portrays a series of 9 or 10 early and 9 or 10 latecorrelators surrounding prompt correlator 74 to achieve the ±5 chipcapture window surrounding prompt correlator 74 in 20 half chip steps. Adifferent number of correlators and other delays would also work withthe present invention.

Use of a plurality of fixed delays of one half chip width permit theimmediate reacquisition of signals from a satellite to within anaccuracy of one half chip width. In accordance with satellite signals 72as presently provided by the NAVSTAR satellites, one half chip widthrepresents about 150 meters of maximum position error. It is possible tosubstantially reduce the maximum position error, and/or the speed ofprocessing the data, by using fixed delays of a different amount ofdelay, e.g. fixed delays of one third, one quarter, one fifth or someother value of a chip width.

Conventional approaches for different modes of operation, switch betweenwide and narrow delays at acquisition and/or reacquisition in order toprovide a compromise between the width of the capture window and thenumber of correlations required for the desired range. In accordancewith the present invention, a new technique is used which permits theconvenient use of fixed, chip width delays to provide a finer gradationof correlation steps. In particular, as shown in FIG. 4, two sets ofhalf width delays are used to provide the equivalent of a set of quarterwidth delays. The number of sets of fixed delays and the offset betweenthem may be selected in accordance with the requirements of theapplication being addressed.

Referring now to FIG. 4, a first plurality of sets of n Code Samples 80are derived directly from code generator 76, delayed from each other by½ chip width delays 78 and correlated with n Signal Samples 75 inexclusive OR (or NOR) correlators 74 as provided in FIG. 3. Forconvenience of explanation and drawing, the outputs from this first setof set of n Code Samples 80 are shown applied to summers 84 to indicatethat the correlation products produced in exclusive OR correlators 74from each such set of n Code Samples 80 are applied to threshold test 82via summers 84. All such correlation products are applied, but forclarity only the correlation products having no delay, the predictedprompt or k/2th delay and the kth delay are depicted. The correlationproducts from this first plurality of sets of n Code Samples 80 arespaced apart by ½ chip width delay as noted above.

In addition, in accordance with the present invention, additional setsof correlation products at different spacings are available by use ofone or more additional sets of ½ chip delays 78 by, for example,tracking the same satellite in two or more channels offset in time fromeach other. It is important to note again that other delays and/oroffsets may also conveniently be used and the delays need not all be thesame.

In particular, a second plurality of sets of n Code Samples 86 arederived from code generator 76 and delayed from each other by ½ chipwidth delays 78. However, the delays in the second sets of n CodeSamples 86 are offset from the delays in the first sets of n CodeSamples 80 by a fixed amount, such as a ¼ chip width delay, by insertionof ¼ chip width delay 79 between code generator 76 and the first set ofn code samples in sets of n Code Samples 86. This results in each of thesamples in sets of n Code Samples 86 falling halfway between two of thesets of n Code Samples 80. As shown in FIG. 4 only k-1 sets of n CodeSamples 86 are required with k sets of n Code Samples 80.

Each of the sets of n Code Samples 84 are correlated with n SignalSamples 75 in exclusive OR correlators 74 as provided in FIG. 3 toproduce correlation products which are then summed by additional summers84. As noted above, the dashed lines between each of the sets of codesamples and summers 84 are used to indicate that the correlation productbetween that set of code samples and n Signal Samples 75 is applied to aparticular one of summers 84. As can then easily be understood from FIG.4, correlation products separated from each other by ¼ chip widthdelays, from the 0th delay to kth delay, are produced using sets of ½chip width delays and a single ¼ chip delay (which may represent theoffset delay between two channels) and after individual summation areapplied to threshold test 82 to determine which delay represents thecurrently prompt delay of satellite signals 72 from a satellite beingreacquired by GPS car system module 26.

The second set of ½ chip delays may easily be implemented by having asecond channel track the same satellite, offset, however by ¼ chip widthdelay 79.

In this way, the range of delay within which a satellite signal lock maybe acquired, maintained and/or reacquired may be reduced from ±½ chipwidth, to about ±¼ chip width, which permits faster pull in to lock,i.e. when the tracking has been optimized and range error reduced tominimum.

It is important to note the seamless integration of tracking andreacquisition provided by the present invention in that the samecorrelations are used for tracking and reacquisition and the relatedspeed of capture and lock and simplicity provided thereby. The abilityto rapidly reacquire within a capture window so that one of thecorrelations may immediately be used as a prompt correlation, speeds upall data acquisitions thereafter. It is also convenient to utilize afirst plurality of sets of n Code Samples 80 for tracking and, whensatellite signals 72 are lost, provide additional accuracy inreacquisition by using a second plurality of sets of n Code Samples suchas sets of n Code Samples 84. In particular, the same plurality of setsof n Code Samples 84 may be used for reacquisition of signals 72 fordifferent satellites at different times in order to reduce the totalnumber of components and steps required to produce all the necessarycorrelations and summations.

In operation, GPS car system module 26 continuously attempts to trackand reacquire the signals from satellite 19 in SatTRAK channel 38 whilesatellite 19 is obscured from view. As car 10 passes throughintersection 22, the line of sight to satellite 19 is momentarily notobscured by buildings 21. Whenever any of the correlations performed inSatTRAK channel 38 indicate that the satellite signals are beingreceived with sufficient strength so that the correlation products fromsome of the correlators are above threshold, reacquisition isimmediately accomplished. Reacquisition occurs when the correlatoroutput indicating the largest magnitude is selected as the new promptcorrelator. Conventional techniques for improving the quality of thedata are then employed.

The data from satellite 19 is used to immediately, after a settling timefor lock, update the GPS data and correct the currently known positioninformation derived therefrom. Even if satellite 19 is then againimmediately obscured, the update information derived during travelthrough the intersection by fast reacquisition provides a substantialimprovement in accuracy of the GPS determined position. This will permitGPS car system module 26 to continue accurate navigation even throughotherwise very difficult areas, such as city streets.

Although the use of single satellite navigation data by cross-track holdand then updating a satellite data by detecting turns and/or immediatelyreacquiring satellite signals in intersections have all been describedseparately, they are also very useful in combination. Terrestrialnavigation systems, using GPS receivers in a stand alone mode, aided bymap displays and data bases and/or aided by external sensors such asinertial navigation systems may benefit from the use of combinations ofone or more such modes. In a preferred embodiment of the presentinvention, all three techniques are combined to maximize the ability ofthe car navigation system to provide accurate and useful navigation datawhile traversing a difficult environment such as city streets.

Referring now to FIG. 5, a preferred embodiment of the present inventionis described in which major portions of SatTRAK channels 38, 40, 42 and44 and SatProcessor 46 of the present invention are implemented in anApplication Specific Integrated Circuit or ASIC 102. Many of thefunctions of a conventional satellite processor may still, however, beperformed in software. The particular implementation depicted provides a12 channel GPS acquisition and tracking system with fast reacquisitioncapabilities as described above while substantially reducing the numberof gates required on the ASIC to implement this system.

The signals received by GPS antenna 28 are digitized and form a digitalcomposite of signals received from all satellites in view to producesample data 100 which is at a frequency of 37.33 f₀ where f₀ is the chiprate of the C/A code applied to each GPS satellite. For convenience, thefrequencies described below will be designated in terms of multiples off₀. Each of 12 Space Vehicles (SVs) or satellites are tracked in ASIC102 under the control of Central Processing Unit, or CPU, 101 whichprovides control signals and data to ASIC 102. In particular, CPU 101provides data regarding the predicted Doppler shifts and C/A codeapplied to each SV to Random Access Memory, or RAM, R1 103 associatedwith ASIC 102 which provides the data to RAM R2 105 at designated times.RAM R2 105 provides data to and receives data from ASIC 102, permittingCPU 101 data updating and ASIC 102 processing of old data to operatesimultaneously. RAM R2 105 is used as a buffer by ASIC 102 primarily tostore intermediate values of signals during processing. Otherconventional portions of a micro-computer including a CPU are not shownbut conveniently may include devices operating software implementing thesingle satellite, cross-track hold and other techniques described aboveas well as other functions of SatProcessor 46.

Sample data 100 is applied to C/A code acquisition, tracking andreacquisition block CACAPT 104 in ASIC 102 where it is split intoin-phase and quadrature-phase, or I and Q, signals at baseband by I/Qsplitter 106. After processing by CACAPT 104, the I,Q signals arerotated for Doppler shift in 12 channel Doppler Block 108 whichseparately compensates for the expected Doppler frequency shifts of eachof the 12 SVs which can be tracked.

The Doppler rotated I,Q signals for each SV are then applied toCorrelator Block 110 where each signal sample, which is from one of the12 SVs, is correlated in a multiplexed fashion with 20 delayed versionsof the C/A code, produced by 12 channel Coder Block 112, for that SV.During each segment of time, as described below with regard to FIG. 11in greater detail, Correlator Block 110 performs 240 C/A codecorrelations in accumulator 175 to enhance the speed of acquisition andreacquisition. The output of Correlator Block 110 is applied to IQACCUMBlock 114, and the output of IQACCUM Block 114 is applied to IQSQACCUM116, in Accumulator Block 115. IQACCUM Block 114 is convenientlyconfigured from another block of RAM associated with ASIC 102,identified herein as RAM 3. Similarly, IQSQACCUM 116 is convenientlyconfigured from another block of RAM associated with ASIC 102,identified herein as RAM 4.

Accumulator Block 115 operates in different fashions during acquisition,tracking and reacquisition modes under the direction of CPU 101. Duringacquisition mode, Coder Block 112 is caused to sequence through as manysets of 240 different codes delays as necessary to acquire the satellitesignals from a particular space vehicle. That is, as many sets of 240different delays are correlated in Correlator Block 110 to provideIQSQACCUM 116 with an appropriate correlation output whose powerindicates that correlation has been achieved with that satellite. Theprocess is then repeated-for each satellite to be acquired. Forconvenience, all delays may be tested.

During reacquisition, a single set of 20 delays are correlated inCorrelator Block 110 to determine if one such delay provides a peakvalue above a predetermined threshold to indicate that a correlation hasbeen achieved and the satellite thereby reacquired. The reacquisitionmode operates transparently within the tracking mode in that a set of 20delays are correlated in Correlator Block 110. If tracking ismaintained, the peak signal may migrate from a particular delay to thenext adjacent delay but will be maintained within the current set of 20delays being correlated. It is convenient to consider the delayproducing the signal with the greatest magnitude as the prompt delay,producing the prompt correlation product. The signals produced by onemore and one less delay then become the early and late correlationproducts which may be processed in a conventional manner to maintainlock with each satellite.

If the signal from the satellite is temporarily obscured or lost for anyother reason, the then current set of 20 delays is correlated andsearched for a peak of sufficient magnitude to indicate reacquisition.The Doppler and code values are continuously updated based upon the lastavailable position information including velocity, and the correlationsare performed, until the satellite signal is reacquired or sufficienttime has elapsed so that the satellite signal is considered lost.

The operation and configuration of ASIC 102 will now be described ingreater detail with regard to the in-phase or I signal path. Thequadrature phase or Q signal path is identical and need not beseparately described.

Within CACAPT 104, sample data 100 is applied at 37.33f₀ to I/Q splitter106 to produce a 2 bit signal at 18.67f₀ which is further reduced to 2f₀by Digital Filter 118 which operates by adding sets of 10, 9 and 9samples which are summed, quantized, and then stored serially in 11sample deep buffer 120. When 11 sample deep buffer 120 is filled, thedata is transferred in a parallel fashion to an identical buffer, calledparallel block 122, for Doppler rotation. Data is therefore transferredout of 11 sample deep buffer 120 when 11 samples are received, that is,at a chip rate of {fraction (1/11)}th of 2f₀ or approximately 0.18f₀. 11sample deep buffer 120 operates as a serial to parallel converter whileparallel block 122 operates as a parallel to serial converter. Thisresults in 186 parallel transfers per msec.

Data is shifted out of parallel block 122 at 24f₀ to 12 channel DopplerBlock 108 so that the Least Significant Bit or LSB of the serialconverter, parallel block 122, is the output of CACAPT 104 in the formof CapIOut and CapQOut which are applied as CACAPT Data output 123 to 12channel Doppler Block 108. The increase in chip rate from 2f₀ to 24f₀provides an operating speed magnification of 12 as will be describedbelow in greater detail.

Referring now also to FIG. 6, 12 channel Doppler Block 108 is nowdescribed in greater detail. Doppler Block 108 receives satellitespecific CACAPT Data output 123 including CapIOut and CapQOut fromCACAPT 104 for storage in Doppler Register 124. Satellite or sourcespecific predicted Doppler phase, after processing by Carrier NumericalControl Oscillator or NCO 125 and sine/cosine look-up table 134, is alsoapplied to Doppler Register 124 where it is added to CapIOut and CapQOutfor the same SV (or other source) to form dopIOut and dopQOut. WithinDoppler Block 108, Carrier_NCO 125 operates at an effective rate of 2f₀for each satellite channel because the data sample rate is 2f₀.

For each SV, CPU 101 stores the satellite specific predicted carrierphase dopPhaseParam, and predicted carrier frequency dopFreqParam, inRAM R2 105. Sat_Mem 186 then transfers the dopPhaseParam anddopFreqParam as shown in FIG. 9 to Carrier Phase Register 126 andCarrier Phase Output Buffer 128, respectively, at each 1 msec boundary.In the drawings, the number of the first and last bit of the signal isprovided in parenthesis, separated by a full colon, in accordance withcurrent conventions. Therefore, dopFreqParam is a 24 bit digital value,the MSB of which is bit number 23 and the LSB of which is bit number 0.Adder 130 adds carrier phase to carrier frequency, derived fromdopPhaseParam and dopFreqParam, to produce the current carrier phasevalue in Carrier Phase Register 126 shown as Carrier_NCO.

The four Most Significant Bits or MSBs of Carrier_NCO in Carrier PhaseRegister 126 are applied to sine/cosine look-up table 134 which includes24-bit registers for storing its output. The output of sine/cosinelook-up table 134 is applied to Doppler Multiplier 132 in DopplerRegister 124 for Doppler rotation of CACAPT Data output 123 (CapIOut andCapQOut) to produce rotated SV output signals dopIOut and dopQOut.Doppler Register 124 uses Doppler Multiplier 132, as well as four 4-bitregisters, two adders, another pair of 5-bit registers and a quantizerto form dopIOut and dopQOut. Referring for a moment to FIG. 11, dopIOutand dopQOut are applied to parallel converter 166 and rotated SV outputsignal 127 is the output of serial to parallel converter 166 which isapplied directly to 11 bit Holding Register 140.

During each segment of time, the beginning value for the Doppler phaseof each SV is stored in RAM R2 105, retrieved therefrom by Doppler Block108 for the rotation of the SV during that segment. At the end of eachsegment, the end value of Doppler phase is stored in RAM R2 105 for useas the beginning value for the next segment. Under the control of gpsCTl182, Doppler phase value dopP_Next in Carrier Phase Output Buffer 128,saved at the end of each rotation for a particular SV by dopSave, isapplied to Sat_Mem 186 for storage in RAM R2 105 for that SV, to beretrieved by Doppler Block 108 again during the next Doppler rotation ofthat SV in the following segment. The operation of Multiplexer Block 129may be best understood from the description of the triple multiplexingof ASIC 102 associated with FIGS. 10 and 11.

Referring now also to FIG. 7, 12 channel Coder Block 112 includesCoder_NCO 136 and Code Generator 138. Coder_NCO 136, which is similar toCarrier_NCO 125 shown in FIG. 6, creates Gen_Enable whenever PhaseAccumulator 148 overflows. Gen_Enable is the MSB of the output of PhaseAccumulator 148 and is applied to Code Generator 138.

In particular, under the control of gpsCTl 182, Sat_Mem 186 applies thesatellite specific 24 bit code frequency parameter, coderFreqParam, andthe 24 bit satellite specific code phase parameter, codePhaseParam, ateach 1 msec edge to Coder_NCO 136 from RAM R2 105. CoderFreqParam isadded to codePhaseParam effectively at 4f₀ per channel in Phase Adder150 even though codePhaseParam operates at 48f₀ during tracking andreacquisition. A pulse can be generated for Gen_Enable between 0 Hz and4f₀ Hz. In order to generate Gen_Enable at 2f₀, the value of half thebits (23:0) of Phase Accumulator 148 must be loaded in ascoderFreqParam.

The LSB of codePhaseParam represents {fraction (1/256)}th of a C/A codechip. CodePhaseParam initializes the contents of Phase Accumulator 148.Gen_Enable is generated whenever Phase Accumulator 148 overflows. PhaseAccumulator 148 is a 25 bit register initialized by the value ofcodePhaseParam when corHoldRegLoad 152 from CPU 101 is active at each 1msec edge when new data is written from CPU 101. The 24 LSBs of 25-bitPhase Accumulator 148 are then added to coderFreqParam in Phase Adder150 and returned to Phase Accumulator 148. Phase Buffer Register 154stores and buffers the contents of Phase Accumulator 148, to produceCoderPNext which is updated whenever codCodeSave 158 from gpsCtl 182 isactive. CoderPNext is applied to Sat_Mem 186 for storage in RAM R2 105.The operation of multiplexer 142 may be best understood from thedescription below of the triple multiplexing of ASIC 102 provided withFIGS. 10 and 11.

Gen_Enable is applied to Code Generator 138 to cause a new code to begenerated. C/A Codes parameters G1 and G2 are parallel loaded from RAMR2 105 by Sat_Mem 186 as g1ParIn and g2ParIn into Code Generator 138 toproduce g1GenOut and g2GenOut which are returned to RAM R2 105 bySat_Mem 186. The bit-0 of both G1 and G2 generators in Code Generator138 are internally XOR=d and generate genSerOut 160 which is seriallyapplied to 11 bit Code Shift Register 170 in Correlator Block 110, asshown in FIG. 5. Code Generator 138 generates the following C/A codes:

G1=1+X3+X10

G2=1+X2+X3+X6+X8+X9+X10.

The output of Code Shift Register 170 is applied to correlators 74, 11bits at a time at 48f₀ so that at least 20 code delays, separated by onehalf chip width, are correlated against each Doppler rotated sample fromeach SV. The increase in chip rate from 2f₀ to 48f₀ provides amagnification factor of 24 as will be described below in greater detail.

Values of G1 and G2 are be stored in RAM R2 105 during each segmentafter correlation with the Doppler rotated sample in correlators 74 forthat SV so that they may then be retrieved by Coder Block 112 during thenext time segment for correlation of the next 11 bit sample from thesame SV.

Referring now also to FIG. 8, Correlator Block 110 is shown in greaterdetail. DopIOut and dopQOut in the rotated SV output from Doppler Block108 are applied to serial to parallel converter 166 which is thenparallel loaded to Holding Register 140. GenSerOut 160 from Coder Block112 is applied to Code Shift Register 170 in Correlator Block 110. Thesedata sets represent the Doppler shifted data received from the SV, aswell as the locally generated code for that SV, and are applied toExclusive NOR gate correlator 74 for correlation under control of gpsCtl182.

The output of correlator 74 is applied to Adder 174 and combined in BitCombiner 176 to corIOut 178 and corQOut 180 which are applied to IQACCUMBlock 114 and IQSQACCUM 116 shown in FIG. 5. Adder 174 and Bit Combiner176 operate as a partial accumulator as indicated by accumulator 175 inFIG. 5.

Referring now also to FIG. 9, on overview of the operation of ASIC 102is shown. A dedicated set of on-chip logic controls the operation ofASIC 102 and is identified herein as gpsctl 182. In particular, underthe control of gpsctl 182, sample data 100 from the GPS satellites isapplied to CACAPT 104 where it is separated and decimated into I and Qdata streams to form CACAPT Data output 123. SV data 123 is rotated forthe predicted Doppler shift of each SV to produce rotated SV outputsignals dopIOut and dopQOut which are correlated with genSerOut 160 fromCoder Block 112 in correlators 74. CorIOut 178 and corQOut 180 fromcorrelators 74 are accumulated in IQACCUM Block 114 and IQSQACCUM 116 toproduce output 184 to CPU 101.

As will be further described below in greater detail, a portion ofmemory is used for Sat_Mem 186 which stores and provides the Dopplershift and code information required during multiplexing.

In operation, every millisecond is divided into 186 segments, each ofwhich includes 264 clocks. Within these 264 clocks, 12 channels areprocessed with each channel taking 22 clocks to compute 22 differentcorrelations or delays. Only 20 of these 22 correlations are stored andused for subsequent processing. For each channel, gpsCtl 182 controlsthe loading of Carrier_NCO 125 in Doppler Block 108 using dopLoad anddopSave. Similarly, gpsctl 182 controls the loading of Coder_NCO 136 inCoder Block 112 via corHoldRegLoad and corCodeSave. The flow of datathrough Correlator Block 110 is controlled with serialShiftClk, and alsocorHoldRegLoad and codCodeSave. Control signals are applied to IQACCUMBlock 114 and IQSQACCUM 116 for each channel and include startsegment,startChan, resetAcc, peak, iqsq, wrchan, ShiftSelIqSq and acq_mode.Within each segment, gpsCtl 182 provides the periodic signalseng_capShiftClk, capLoad, syncpulse, serialShiftClk to CACAPT 104 torepackage incoming satellite data samples into groups of 11 half chipsamples.

All accesses initiated by gpsCtl 182 are processed by Sat_Mem 186 togenerate read/write control and address signals for RAM R1 103 and RAMR2 105. GpsCtl 182 controls the flow of data through all data pathstogether with Sat_Mem 186 and manages the access of channel parametersstored in RAM R1 103 and RAM R2 105. RAM R1 103 is written to by theuser to define the channel parameters that will be loaded to RAM R2 105at the end of the corresponding integration or accumulation time. RAM R2105 is used by the data path as a scratchpad to store the intermediatevalues of the various channel parameters during processing.

Data read out of RAM R2 105 is sent to the various parameter registersin Doppler Block 108, Coder Block 112, Correlator Block 110 and gpsCtl182 under the control of Sat_Mem 186. Data from these blocks and RAM1190 are multiplexed at the input to the write port of RAM R2 105. RAM R1103 is a 16×108 asynchronous dual port ram used for the parameters forall 12 channels while RAM2 192 is another 16×108 asynchronous dual portram used for storing intermediate values of the satellite parametersduring processing, while switching from one channel to the next.

Referring now to FIG. 10, the system of the present invention includes amultiplexed data path in order to reduce the size and complexity of ASIC102 on which the majority of the parts of the system can be provided.Conventional receiver designs have multiplexed a single set ofcorrelators for use for each of the separate channels in which an SV istracked in order to reduce the number of correlators required. The useof the system of the present invention reduces the million or more gatesthat would be required-for a conventional configuration down to amanageable number, on the order of about less than 100,000.

In accordance with the present invention, in addition to multiplexingthe satellite channels in a manner in which no data is lost, the codedelay correlations are also multiplexed. That is, conventional receiversuse two or three correlators to provide early, late and/or promptcorrelations for each SV. The present invention multiplexes a pluralityof code delays in order to provide far more code delay correlations thanhave been available in conventional systems without substantiallymultiplying the hardware, or chip area on ASIC 102 required by thenumber of gates used.

The multiplexing of code delays permits the wide capture windowdescribed above with regard to FIGS. 3 and 4 that permits rapid SVreacquisition. In particular, 20 delays such as ½ chip delays areprovided and constantly monitored for each SV so that GPS data can beacquired even during brief glimpses of the SV, for example, when car 10is in intersection 22 as shown in FIG. 1. The SV can be reacquired anduseful data obtained because the modeling of the vehicle's position onroadway 12 is sufficiently accurate to keep the predicted code andDoppler values for a previous acquired and currently obscured SV withina window of ±10 half chip code delays. In this way, data obtained duringreacquisition can be used directly as GPS data. That is, thereacquisition mode is transparent to the tracking mode. The GPS data isacquired whenever available without substantial lost time forreacquisition.

Further, the operation of satellite tracking is itself multiplexed foreach set of data for all 12 channels in order to further substantiallyreduce the ASIC gate count. That is, only a small portion of the bits inthe C/A code is processed at one time for all 12 SVs. In order todigitally process the signals received, the digital representations ofthese signals must be processed in registers and buffers capable ofstoring the digital data. The C/A code contains 1023 bits in eachrepetition which lasts 1 msec. If all 1023 bits were to be processed atonce, registers 1023 bits wide would be required. Such registers wouldbe expensive in cost and gate count and quite cumbersome. In accordancewith the third level of multiplexing used in the triply multiplexedreceiver configuration of the present invention, a smaller register ismultiplexed to handle different portions of the 1023 bits of the C/Acode. This means the smaller register is used many times during each 1msec repetition of the C/A code to process enough smaller samples of thedata received so that within each msec all 1023 bits can be processed.

In the preferred embodiment described above particularly in FIGS. 3 to9, a configuration using 11 bits registers was used so that eachregister is used 186 times per msec to process all 1023 bits of a C/Acode repetition. Each {fraction (1/186)}th of a msec is called asegment. The tracking of each SV is therefore multiplexed 186 times byprocessing the 11 bits in each register during each segment. Inaddition, in the preferred embodiment, 12 channels are used to track amaximum of 12 SVs. This requires that each 11 bit segment is multiplexed12 times during that segment to apply a Doppler rotation for each SV.

Further, each channel is further multiplexed by a factor of 22 toprovide a substantial plurality of different code delays. This requiresthat the Doppler rotated sample for each SV is correlated 22 times withdifferent C/A Code delays before the Doppler rotated sample for the nextchannel is produced. In this manner, 22 different code phases may betested for each of 12 SV during each of 186 segments to provide realtime data with only 11 bit wide registers by processing each register186 times per msec.

It is important to note that the processing of the present inventionoccurs during a particular segment, i.e. a {fraction (1/186)}th of arepetition of the C/A code, during the length of time required for thesegment to be collected. In this optimized manner, no data is lostduring tracking or reacquisition or switching between these statesbecause the data being processed in any particular segment is at most 11half chips delays old.

Referring now to FIGS. 10 and 11, the output of Digital Filter 118 shownin FIG. 5 is sample data stream 119 at 2f₀. The chip rate of the C/Amodulation of the signals 100 from the SVs is at f₀. In order to avoidloss of any data, the SV signals must be sampled at least at theirNyquist rate, that is, at twice the chip rate of the modulation ofinterest which is 2f₀. Although sample data stream 119 can be operatedat a higher chip rate than the Nyquist rate, which is twice the chiprate, there is no advantage in doing so.

Sample data stream 119 is therefore a series of samples of the digitizedand filtered SV data at twice the chip rate of the C/A code, that is,each sample in sample data stream 119 has a width equal to one half of aC/A code chip. The number of bits in each msec or cycle of code insample data stream 119 is twice the number of bits in the modulation,i.e. 2046 bits each representing one half of a C/A code chip. Inaccordance with the multiplexing scheme of the preferred embodimentbeing disclosed, the data is processed in 11 bit segments, and sampledata stream 119 is therefore applied serially to 11 bit (10:0) registervalue buffer 120. The time required to serially store 11 bits out of atotal of 2046 bits in the 2f₀ data stream is 1÷(2046÷11=186) or{fraction (1/186)}th of a msec.

During the time the first set of 11 sample bits are being stored in 11sample deep buffer 120, no bits are available for processing. After thefirst 11 sample bits are serially received and serially stored, the 11sample bits are transferred in parallel to parallel block 122. Thisparallel operation therefore occurs every {fraction (1/186)}th of a msecor at a rate of approximately 0.18f₀. Each {fraction (1/186)}th of amsec is called a time segment or segment and is the unit of processingfor most of the operations. The 1023 chip C/A code of each of thesatellites in the composite signal received is processed in 11 half chipbits. Dividing the msec repetition rate of the C/A code into 186 timesegments multiplexes each of the 11 bit registers by a multiplexingfactor of 186.

CACAPT Data output 123 from parallel block 122 is processed in DopplerBlock 108 at a much faster chip rate, for example at 24f₀. That is, the11 bits of sample data in each segment of time is multiplexed by afactor of 12 to permit 12 different operations to be performed to thatset of 11 bits of data. In particular, in Doppler Block 108, CapIOut andCapQout of CACAPT Data output 123 are multiplied in Doppler Register 124by twelve different Doppler shifts so that within each segment twelvedifferent Doppler rotations are performed.

Each different Doppler shift represents the predicted Doppler rotationrequired for each of the maximum of 12 different SVs that can betracked. The increase in processing chip rate from 2f₀ to 24f₀multiplexes the processing for each of 12 channels of data. It isimportant to note that the multiplexing to permit one channel to operateas 12 multiplexed or virtual channels each representing a different SVis applied only after the input signals are multiplexed, that is, brokeninto 186 time segments each including 11 half chip width bits. In thisway, the multiplexing for 12 channels or satellites is easilyaccomplished with relatively inexpensive 11 bit registers without lossof time or data. The selection of the number of sampling to be aninteger division of the number of code bits per period is important toachieve these goals. Multiplexer Block 129 in Carrier_NCO 125 controlsthe timing of this multiplexing under the direction of gpsCtl 182.

The output of Doppler Block 108, signals dopIOut and dopQOut, areapplied to serial to parallel converter 166 within Correlator Block 110.Each rotated SV output signal 127 represents the rotated signal from asingle SV and 12 such rotated SV output signals 127 are produced in eachsegment of time.

Rotated SV output signal 127 is loaded in parallel fashion into HoldingRegister 140 in Correlator Block 110. The input to Exclusive NOR gatecorrelator 74 is therefore an 11 bit wide signal which is retained for{fraction (1/12)}th of a time segment as one input to Exclusive NOR gatecorrelator 74.

Correlator 74 is a series of 11 separate one bit correlators which alloperate in parallel. One input is rotated SV output signal 127 while theother 11 bit input is provided by 11 one bit genSerOut 160 output bitsfrom Coder Block 112. During the {fraction (1/12)} of a time segmentprovided for operation on the rotated SV output signal 127 for aparticular satellite, the code for that SV is produced serially by CodeGenerator 138 and applied to Code Shift Register 170.

At the beginning of the correlation for a particular channel, 11 bits ofthe code for that SV have been shifted into Code Shift Register 170 andare available therein for correlation. Every {fraction (1/22)}nd of achannel (that is, a {fraction (1/12)} of a segment) each of the 11 bitsin Code Shift Register 170 are correlated in one of 11 one bit exclusiveNor gates in Exclusive NOR gate correlator 74. This produces 11correlator output bits, the sum of which indicates the magnitude of thecorrelation between the rotated SV output signal 127 and that codephase. These 11 correlation sums produced in parallel are summed inparallel and stored in the first of 22 summers related to that SV inAccumulator Block 115.

During the next or second {fraction (1/22)}nd of a channel, CodeGenerator 138 produces the next bit for the C/A code for that SV. Thisnext bit is applied serially to Code Shift Register 170. At this time,10 bits from the first correlation remain in Code Shift Register 170 andtogether with the newest bit form another 11 bit sample of the expectedcode for that SV, delayed from the previous 11 bit sample by the timerequired to generate 1 bit, that is, one half chip width at the ratecode is produced, 48f₀. The second sample is therefore a one half chipdelayed version of the code, delayed one half chip width from theprevious 11 bit samples. It is important to note that the two 11 bitcode samples just described differ only in that a new bit was shifted inat one end of the register to shift out the MSB at the other end of theregister.

The 11 bit correlation product of the same rotated SV output signal 127and the second 11 bit sample of code is then stored in the second of the22 summers related to that SV in Accumulator Block 115. Thereafter, theremaining 20 serial shifts of the genSerOut 160 from Code Generator 138are correlated against the same rotated SV output signal 127 to produce20 more sums of 11 bit correlations for storage in Accumulator Block 115for that SV. The result is that 22 values are then available withinAccumulator Block 115 for processing, each value is a measure of thecorrelation of the signals from one SV with 22 different code phases ordelays, each separated by one half chip width.

During the next {fraction (1/12)} of a time segment, that is, during theprocessing of the second multiplexed channel, the rotated SV outputsignal 127 for the next SV, is applied to Holding Register 140 forcorrelation with 22 different one half chip delays of the code generatedfor that satellite. At the end of a segment, Accumulator Block 115includes a matrix of 12 by 20 different sums. In one implementation ofthe present inventions it has been found to be convenient to save only20 out of the 22 possible code delay correlation results. The 12 rows of20 sums represent the measure of correlation for each of the 12 SVs at20 code phases or delays.

In summary, the data path for the present invention is triplymultiplexed in that

(a) each msec, which represents 1023 bits of C/A code, is sliced into186 to form the 186 segments in a msec of sample so that only 11 halfchip wide sample bits are processed at one time;

(b) each segment is then multiplexed by 12 so that each such 11 bitsample is rotated for twelve different sources;

(c) the rotated 11 bit sample for each source is correlated against 20sets of different code delays for that source to multiplex within eachchannel by 20; and

(d) the sum of the correlation products for each delay in each channelare then summed to produce the accumulated correlation output.

Although 22 different delays are available, it is convenient to use 20such delays, or code phase theories for testing the rotated satellitesignal. The correlation product having the greatest magnitude for eachchannel after accumulation, that is, the largest of the 20 sums of 11bits stored in Accumulator Block 115 for each channel may then bedetected by its magnitude, for example by a peak detector, to determinewhich delay theory is the most accurate. The peak sum represents theon-time or prompt correlation for that SV.

Turning now specifically to FIG. 11, the triple multiplexing scheme ofthe present invention may easily be understood by looking at the slicesof time resulting from each of the multiplexing operations. Within eachmsec, the C/A code for each particular satellite has 1023 bits. In orderto preserve all necessary information, the satellite signals aresampled, in a digital composite of signals from all satellites, at theNyquist rate at 2f₀ to produce 2046 half chip wide sample bits.

Each sequential set of eleven sample bits are processed together as asegment of time, the length of which is equal to 1/(2046÷11) of a msec,i.e. one {fraction (1/186)}th of a msec. After processing of the 186thsegment in a msec all necessary data has been extracted and the 11 bitsample for the next segment is available. Although the partial sumsaccumulated over each msec in Accumulator Block 115 may only beevaluated at the end of a msec, no data is lost and the results are only1 segment late. That is, since it takes 1 segment to fill 11 sample deepbuffer 120 and transfer the 11 bit sample to parallel block 122, thedata from the first 11 bit sample is being processed while the data forthe second 11 bit sample is being collected. Even if the system operatedfor a year, the sampled being processed to provide position informationis still only one time segment old.

The 11 bits of each segment are multiplexed for each SV by being timedivision multiplexed during Doppler rotation. That is, the 11 bit sampleof segment 1 is used to provide 12 different Doppler shifted outputs sothat a single 11 bit segment sample is used 12 times to produce 12different satellite specific Doppler rotated versions, assuming all 12satellites are in view or being modeled. The operations for one channelthen require one twelfth of a segment. It is critical to note that eachsegment only produces a partial result and that the 12 partial resultsduring each segment must be summed at the end of each msec to providevalid output data.

Each of the operations on one particular channel in a segment are timedivision multiplexed by a factor of 22 so that 22 different code delaysfor that partial sum for that satellite can be tested. The peak sum ofthese 22 correlations can however be detected by magnitude immediatelyif necessary to select the most likely delay for that channel. In thepresent embodiment, the information for that channel is only valid onceper msec when summed or accumulated so that there may not be asubstantial advantage in peak detected with a particular segment. Insome GPS applications and in other spread spectrum applications, such aswireless communications, it may be desirable if strong signals arepresent to accumulate and transfer the sum of the accumulations for eachsource from R3 to R4 more often than once per code repetition rate. Thetime required to evaluate a particular code phase delay or theory isonly {fraction (1/22)}nd of the time required per channel per segment or{fraction (1/22)}nd of {fraction (1/12)} of {fraction (1/186)}th of amsec. This speed of operation is more easily achieved because the 11 onebit correlations required are produced in parallel. Similarly, the speedof generation of the different code delays for a particular SV is moreeasily accomplished in accordance with the present invention becauseeach 11 bit code delay sample is automatically produced when each singlenew bit, i.e. each new genSerOut 160, is shifted into Code ShiftRegister 170.

The selection of the magnitudes or multiplexing factors used in eachlevel of multiplexing is not arbitrary. The larger the number ofsegments, the smaller the required size or depth of the registers needfor each sample. By using a code repetition multiplexing factor of 186,that is, by dividing the 2046 bits of a 2f₀ by 186, only 11 sample bit,need to be evaluated at a time.

The number of required channels is bounded pragmatically by the factthat at least 4 SVs must be in view at the same time to determineposition accurately in three dimensions. Time is the fourth unknownwhich must be determined along with each of the three dimensionsalthough provisions for estimating, modeling and/or updating theposition information as described above so that position information maybe accurately provided even during periods when less than 4 satellitesare concurrently in view.

The constellation of 24 NAVSTAR satellites in use are arranged to coverthe earth so that a maximum of 12 such satellites may be in view at anyone location at any particular time. The maximum number of pragmaticallyuseful channels is, for this reason, no less than about 12 channels. Theselected channel multiplexing factor used in the channel level ofmultiplexing in the embodiment shown herein is therefore a factor of 12.

The number of different code delays is bounded at the low end by anabsolute minimum of 1 so that if the exact delay can somehow bemaintained, the only necessary correlation would be the on-time orprompt correlation. Conventional GPS receiver systems use at least 2 or3 different code delays so that conventional tracking techniques, forexample those which use early, prompt and late correlations to centerthe prompt correlation within ±1 delay, may be employed.

In accordance with the present invention, a substantially greater numberof different code delays, or delay theories, are tested so that fastreacquisition may be accomplished as described above with regard toFIGS. 3 and 4. Although for the particular preferred embodimentdescribed herein, it was determined that a total of 20 different delays,each separated in time by one half the width of a C/A code chip, i.e. ½of {fraction (1/2046)} of one msec, a code delay multiplexing factor of22 was selected because the relationship between each of the 3multiplexing factors is also important.

The product of the three multiplexing factors, code repetitionmultiplexing factor, channel multiplexing factor and code delaymultiplexing factor should optimally be an even integer multiple of thenumber of bits in each repetition of the spread spectrum modulation. Aneven integer multiple is required because samples must be taken at twicethe chip rate, i.e. at the Nyquist rate, in order to avoid data lossfrom sampling at a slower rate. Although multiplexing factors can beused successfully even if the product is not exactly equal to an eveninteger multiple, data loss or unnecessary complexity and costs mayresult.

In the particular embodiment shown, the spread spectrum code of interestis the C/A code, each repetition of which includes 1023 bits. Inaccordance with the triple multiplexing product rule discussed above,the product of the three multiplexing factors must equal an even integermultiple of 1023, such as 2046. In the described embodiment, the coderepetition multiplexing factor is 186, the channel multiplexing factoris 12 and the code delay multiplexing factor is 22. The product of 186multiplied by 12 and then by 22 is 49104 which, when divided by 1023,equals 48. 48 is an even integer and therefore the particular set ofmultiplexing factors used in the present invention provides one ofseveral optimized systems.

The reason this multiplexing factor product rule works well in atri-level multiplexing configuration for C/A code is that there arethree prime factors in 1023. That is, 1023 is the product of three primenumbers, 31, 11 and 3. Each of the three multiplexing factors is evenlydivisible by one of these prime numbers. For example, 186 is divisibleby 31 six times, 12 is divisible by 3 four times and 22 is divisible by11 twice.

Using each prime factor of the number of bits in the sampled bit rate inone of the multiplexing factors yields two or more different families ofmultiplexing configurations for C/A code spread spectrum receivers. Inthe first family, if 11 channels are desired, then either the coderepetition multiplexing factor or the channel multiplexing factor wouldhave to be divisible by 31. Although it may be desirable in certainapplications to use 31 or 62 different code delays, there is asubstantial advantage in making the code repetition multiplexing factoras large as possible. This reduces the number of bits required to besaved and processed in each segment. By selecting the code repetitionmultiplexing factor to be a multiple of 31, the number of delaysactually used can be more easily controlled because the code delaymultiplexing factor could be any multiple of 3.

In the other convenient family, 6, 9, 12, 15 or 18 satellite channelsare desired so that the channel multiplexing factor is an integralmultiple of 3. This permits the code delay multiplexing factor to be afactor of 11 while the code repetition multiplexing factor is a factorof 31. The particular embodiment described in the specification above isin this family.

Another constraint on the selection of multiplexing factors is the speedof operation of the lowest level of multiplexing. In the embodimentdisclosed, the third level of multiplexing operates at 48f₀. The clockspeed of the hardware implementation must be sufficient to permitoperation at this speed. As faster and faster on chip components aredeveloped, higher clock speeds may be used to accomplish the highestspeed processing and larger multiples may be used. For example, withcomponents in the high speed processing sections such as CorrelatorBlock 110 capable of operation at higher rates at multiples of f₀, suchas at 96f₀, the code repetition multiplexing factor could be doubled toproduce 24 channels with 20 delays or taps or 12 channels with 40 delaysor taps or 11 channels with 6 bits and 22 taps.

The system configuration may also be viewed from the standpoint of atime or speed magnification. Operation at the third multiplexing levelat 48f₀ is 24 times faster than the chip rate of the 2f₀ sample beingprocessed. This amplification factor of 24 permits a hardwaremultiplexing or gate compression factor of 24. The number of gates onASIC 102, or other devices for implementation the present invention, isreduced essentially in direct proportion to the magnification factor.All other factors being equal, the surface area of a chip operated at48f₀ is on the order of {fraction (1/24)}th of the surface area thatwould be required to operate at 2f₀. Similarly, an increase in themagnification factor to 96 would permit a reduction in the required chipsurface real estate required on the order of almost half.

The particular embodiment of the multiple level multiplexing spreadspectrum receiver of the present invention which has been disclosedabove is a GPS receiver. The same invention can be used for other spreadspectrum signals such as wireless telephone signals with dueconsideration for the selections of multiplexing factors based on thebit rate of the spread spectrum code used and the environmental factorsapplicable to that application. The environmental factors for thepresent configuration, such as the pragmatic constraints on the numberof channels and code phases, have been described above.

Referring now to FIG. 12, a block diagram overview of a GPS receiversystem 200 including a preferred embodiment of the digital signalprocessing chip 102 described above, ASIC GSP1 202, and a radiofrequency chip, GRF1 204, combined with other components to form acomplete receiver system according to the present invention.

Associated with ASIC GSP1 202 are SRAM 206, ROM 208 and CPU 101,interconnected by data and address busses 210 and 212 to provide thefunctions of RAM R1 103, RAM R2 105 and Sat_Mem 186 and other requiredfunctions described above with regard, for example, to FIG. 5.

GRF1 204 is including within RF processing subsystem 214 which receivedsatellite signals from GPS antenna 28 and provides sample or GPS data100 to ASIC GSP1 202 which returns an automatic RF gain control signal,AGC 216, back to GRF1 204. Associated with GRF1 204 in RF processingsubsystem 214 are RF filter 218 which applies the signals from GPSantenna 28 to low noise amplifier LNA 220 to output of which is appliedto GRF1 204. In addition, GRF1 204 uses an outboard filter, IF FILTER222 as well as crystal 224. It is important to note that IF FILTER 222may be a low cost, external 2-pole LC (inductance-capacitance) typeintermediate or IF filter, rather than a more expensive and complex 5 or6 pole filter for the following reasons. GPS receiver system 200 uses arelatively wide IF band followed by a decimator or digital filter,Digital Filter 118, as shown for example in CACAPT 104 in FIG. 5.

In particular, the output of LNA 220 is processed by GRF1 204 using IFFILTER 222 to produce GPS data 100 which is applied to CACAPT 104 inASIC GSP1 202. Within ASIC GSP1 202, GPS data 100 is separated into inphase and quadrature phase I and Q signals in I/Q splitter 106. The Isignals are then applied to Digital Filter 118 and the Q signals areprocessed in the same manner as shown in FIG. 5 and described above.

FIG. 13 is a block diagram description of GRF1 204 and FIG. 14 is a pinout of GRF1 204. FIG. 15 is a timing diagram of the AGC interface. FIG.16 provides additional details of a preferred embodiment of GPS receiversystem 200, specifically the interconnections between ASIC GSP1 202 andGRF1 204 as well as the associated circuitry.

Referring now to FIGS. 13 through 16, the SiRFstar™ embodiment of GPSreceiver system 200 may be described as follows:

$ Front End for SiRFstar Architecture $ Cost Effective MMIC IntegrationSnapLock ™ 100 ms On-Chip VCO and Reference Reacquisition OscillatorSingleSat ™ Navigation Low Cost External 2-Pole LC IF Minimum StartupTime Filter Single-Stage L1 to IF Downconversion External 25 ppmReference Crystal $ Seamless Interface $ On-Chip 2-Bit A/DDirect-Connect to GSP1 Improved Weak Signal Tracking Standard 3 or 5 VSupply Improved Jam Immunity Compatible with Standard Active Antennas

The SiRFstar GPS Architecture is designed to meet the demanding needs ofmainstream consumer GPS products. The combination of the SiRFstar GSP1signal processing engine, the SiRFstar GRF1 RF front-end and SiRFstarGSWl software provides a powerful, cost effective GPS solution for awide variety of products. SiRFstar-unique 100 ms SnapLock capabilitiescombined with the 12 channel all-in-view tracking provides maximumavailability of GPS satellite measurements. The SingleSat navigationmode is able to use these measurements to produce GPS position updateseven in the harshest, limited visibility urban canyons. Dual multipathrejection scheme improves position accuracy in these canyons. True 2-bitsignal processing enables FoliageLock™ mode to acquire and track atlower signal levels for operation even under dense foliage.

The high performance firmware that accompanies the chipset takes fulladvantage of the SiRFstar hardware capabilities to provide a completesolution to our customers. The software is modular in design andportable across various processors and operating systems to allow fasttime to market and maximum flexibility of design decisions for addingGPS capability to any product.

Chip Description

The GRF1 is a complete front-end frequency converter for GlobalPositioning System (GPS) receivers. The state-of-the-art design combinesa Low Noise Amplifier (LNA), mixer, 1527.68 MHz Phase Locked Loop (PLL)synthesizer, on-chip frequency reference, IF stage with AGC, 2-bit A/Dconverter and control logic to perform the conversion from RF to digitaloutputs. The GRF1 receives the 1575.42 MHz signal transmitted by GPSsatellites and converts the signal to 47.74 MHz PECL level complementarydigital signals which can be processed by the GSP1 signal processorchip. The 2-bit interface provides superior tracking performance withweak and attenuated signal as well as improved jam immunity.

TABLE 1 Pin Identification Pin Name 1 IF Input 2 {overscore (IF)} Input3 {overscore (MIX)} Output 4 MIX Output 5 Vsa (LNA) 6 {overscore (RF)}Input 7 RF Input 8 Vcc (LNA) 9 Vcc (VCO) 10 Vee (VCO) 11 Vee (CHP) 12CPFB 13 CPSUM 14 CPOUT 15 Vcc (CHP) 16 Vcc (Digital) 17 {overscore(SIGN)} 18 SIGN 19 {overscore (MAG)} 20 MAG 21 {overscore (ACQCLK)} 22ACQCLK 23 {overscore (GPSCLK)} 24 GPSCLK 25 REFIN 26 BYPASS 27 REFOUT 28AGCSTRB 29 AGCDATA 30 AGCCLK 31 Vee (Digital) 32 Vco (IF)

TABLE 2 PIN DESCRIPTION GRF1 Signal Description Pin No. Symbol TypeDescription 1, 2 IF, {overscore (IF)} Inputs Differential IF inputs:balanced inputs to the IF stage; a filter should be placed between theseinputs and the mixer outputs. DC bias to the positive supply must beapplied to these pins. 3, 4 {overscore (MIX)}, MIX Outputs DifferentialIF Outputs; balanced outputs of the LNA/Mixer stage, a filter should beplaced between these outputs and the IF inputs. DO bias to the positivesupply must be applied to these pins. 5 VEE (LNA) Input LNA/Mixer groundpin. 6, 7 {overscore (RF)}, RF Inputs Differential LNA inputs. For bestperformance a balun should be used. Decouping should be to ground. 8VCCLNA Input Postive supply input for LNA/Mixer block. Decoupling toground via 0.01 μF or larger capacitors should be provided. 9 VCCVCOInput Postive supply input for VCO block. Decoupling to ground via 0.01μF or larger capacitors should be provided. 10 VEEVCO Input VCO groundpin. 11 VEECHP Input Charge pump ground pin. 12 CPFB Input Charge pumpfeedback I/O pin. 13 CPSUM Input Summing input for the charge pump. 14CPOUT Output Charge pump output. 15 VCCCHP Input Positive supply inputfor charge pump. Decoupling to ground via 0.01 μF or larger capacitorsshould be provided. 16 VCCDIG Outputs Positive supply input for Digitalcircuitry. For proper operation the digital and analog supplies shouldbe provided by the same regulator. Decoupling to ground via 0.01 μF orlarger capacitors should be provided. 17, 18 {overscore (SIGN)}, SIGNOutputs Differential SIGN bit Outputs. These outputs are PECLcompatible. 19, 20 {overscore (MAG)}, MAG Outputs Differential MAGNITUDEbit Outputs. The magnitude bit is designed to produce a HIGH when theinput level at the A/D is > +/− 50 mV. These outputs are PECLcompatible. 21, 22 {overscore (ACQCLK)}, Ouputs Differential Acquisitonclock ACQCLK outputs. These outputs are PECL compatible. 23, 24{overscore (GSPCLK)}, Outputs Differential x2 reference clock GSPCLKoutputs. These outputs are PECL compatible. 25 REFIN Input Differentialreference clock inputs. External input signals must be applied via ACcoupling. 26 BYPASS Bypass Decoupling 10 Vcc via 0.01 pF or largercapacitor should be provided. 27 REFOUT Output Reference output. Acrystal network may be placed between this output and the REFIN input inlieu of an external oscillator (see FIG. 5). 28 AGCSTRB Input Loadcontrol input. Data is latched into the AGC register on the rising edgeof this input. The input is TTL compatible. 29 AGCDATA Input Data input.A six bit data byte is loaded serially via this data input LSB. Theinput is TTL compatible. 30 AGCCLK Input Clock input. Provides the clockfunction for the three wire AGC control. Data is loaded into a six bitshift register on the negative going edge of this clock. The input isTTL compatible. 31 VEEDIG Input Digital block ground pin. 32 VCCIF InputPositive supply input for IF block. Decoupling to ground via 0.01 μF orlarger capacitors should be provided.

All Vee and Vcc pins should be connected to ensure reliable operation.

Notes on Pin Descriptions

1. All bypassing should be to the positive supply unless otherwisespecified. Capacitors with low dissipation factor should be placed asclose as possible to all power pins.

2. Differential input and output signals should be used for optimalsystem performance.

3. Good RF practices must be followed in the PC board layout, ground andpower planes should be used whenever possible.

4. Vee is commonly referred to as GND.

Functional Description

LNA/Mixer

The GRF1 receives the GPS L1 signal via an external antenna and suitableLNA. The L1 input signal is a Direct Sequence Spread Spectrum (DSSS)signal at 1575.42 MHz with a 1.023 Mbps Bi-Phase Shift Keyed (BPSK)modulated spreading code. The input signal power at the antenna isapproximately −130 dBm (spread over 2.048 MHz), the desired signal isunder the thermal noise floor. The front-end compression point is −30dBm, given adequate external filtering in the IF section, rejection oflarge out-of-band signals is possible.

The LNA/Mixer is totally differential which significantly reduces commonmode interference. With a noise figure of approximately 8 dB and 20 dBconversion gain, cheap relatively high insertion loss filters may beused in the IF. The LNA/Mixer and on-chip 1527.68 MHz PLL produce an IFoutput frequency of 47.74 MHz. The double balanced mixer outputs areopen collectors and therefore require external dc bias to Vcc.

IF Stage

The IF stage provides approximately 75 dB small signal gain. An externalIF filter is required between the LNA/Mixer and IF amplifier stages. TheIF bandpass filter can have a bandwidth between 3 and 12 MHz withoutimpacting performance. The inputs to the IF stage are double ended andrequire dc bias from Vcc. The double balanced I/O provides approximately40 dB noise immunity; therefore, a balanced filter design is highlyrecommended.

A 6-bit register provides 48 dB of gain control (1 dB/bit) and isaccessible via a three wire TTL level interface (AGCCLK, AGCDATA,AGCSTRB). The control bits are serially shifted into the chip LSB firston the falling edge of the AGCCLK. A unique voltage controlled sourcedesign in the IF gain stages provides extremely good gain linearity overtemperature (<0.5 dB). Maximum gain is selected with all zeros loadedinto the register (see FIG. 15 for timing details).

The IF amplifier output is fed to a 2-bit quantizer which provides signand magnitude outputs. The sign and magnitude data bits are latched bythe falling edge of the 38.192 MHz sample clock (see PLL Synthesizer).Differential outputs for this ACQCLK are also provided.

Phase-Locked Loop Synthesizer

The local oscillator, reference GPSCLK, and sample clock are derivedfrom an on-chip PLL synthesizer block. The VCO, dividers, and phasedetector are provided in the chip. All that is needed is an external24.552 MHz reference clock and passive loop filter components.

FIG. 16 shows the chip in a typical configuration. The loop filter isprovided using a charge pump. Two resistors and two capacitors set theloop filter bandwidth. The reference can be produced using a crystal,resistor, and two capacitors, or if better reference stability isrequired an external oscillator may be used. Differential inputs for thereference are available for use with an external oscillator whichprovides significant noise immunity. Differential GSPCLK and ACQCLKoutput signals are provided by the block.

GSP1 Interface

The output side of the GSP1 interface provides clocks and the 2-bitsample data to the GSP1. These signals are all differential to reducenoise and provide better performance. The 2-bit samples are digitallyfiltered which significantly reduces the filtering required in the RFcircuit such that a simple 1 or 2 pole LC filter is sufficient for theIF filter. The GSP1 provides a true 2-bit data path throughout thecorrelation process which enables tracking of extremely weak signals.

The input side of the GSP1 interface is an AGC block which controls thegain in the IF stage in the GRF1. The gain can be set to a fixed valueor allowed to vary according to a software controllable threshold. GSP1monitors the incoming signals and can adjust the gain every 1millisecond, allowing rapid adaptation to a changing signal environment.

TABLE 3 AC Characteristics AC Characteristic Min. Value Max. UnitsConditions LNA/Mixer Conversion Gain 23 25 27 dB (Notes 1, 2) NoiseFigure 8 10 dB (Notes 1, 2) Input Compression (1 dB) −30 −25 dBm (Notes1, 2) Single Ended Input Impedance (Real) 80 Ω (See Notes 1, 3, FIG. 4)Single Ended Input Impedance (Imaginary) 2 pF (See Notes 1, 3, FIG. 4)Differential Output Impendance (Real) >50 KΩ (Note 1) DifferentialOutput Impedance (Imaginary) 2 pF (Note 1) IF Strip Input Impedance min.(Real) 5 >5 KΩ F = 47.74 MHz, (Note 1) Input Compression −60 dBm(Note 1) Small Signet Gain 75 78 dB F = 47.74 MHz, Differential input,Zin = 2 KΩ Gain Linearity +/−0.5 dB F = 47.74 MHz Gain Control Range 4048 52 dB Gain Resolution 0.5 1 1.5 dB/Bit Bandwidth +/−20 MHz Fc = 47.74MHz, (Note 1) A/D Clock Frequency 38.19 MHz Sign Bit Duty Cycle 40 50 60% PLL Synthesizer Spurious −50 dBc (Note 1, Note 4) VCO Gain 1 1.3 1.6GHz/V Phase Detector Gain 60 mV/RAD (Note 1) Reference Input Level 200mVp-p (Note 1) Reference Input Impedence >5 KΩ (Note 1) DigitalInterfaces GPSCLK, ACQCLK outputs Duty Cycle 40 50 60 % TDR, TDF 3 nS Co= 15 pF TACQCYC 28.21 nS Co = 15 pF TGPSEYE 20.36 nS Co = 15 pF TSATSU52.42 nS Co = 15 pF ISINK, ISOURCE 1 2 mA

TABLE 4 AGC Interface Timing Parameter Symbol Min Max Units AGCCLK cycletime T14 161 163 ns AGCDATA setup time T15 61.5 82.5 ns AGCDATA holdtime T16 79.5 80.5 ns AGCSTRB wait time T17 79.5 80.5 ns AGCSTRB pulsetime T18 161 163 ns

Referring now to FIG. 17, a series of graphs of relative correlationamplitude as a function of time offset are shown for direct path and twotypes of multipath interference. These graphs are aligned at a timeoffset of zero, that is, at the time of arrival of the direct pathsignal.

Direct path correlation function 226, in the center of the figure, isthe result of correlating a satellite signal received along a direct,line of sight, path, in the absence of multipath signal(s), with areplica of the C/A code modulation then present on the direct pathsignal. The peak 230 of direct path correlation function 226 is shown atthe origin to represent the actual time of arrival or zero code phase.In practice, this point may be somewhat offset due to filtering andother biases. Peak 230 will be taken as the punctual code phase, thatis, the time of arrival of the PN Code group from a particularsatellite.

Direct path correlation function 226 may be produced for example byoperation of Correlator Block 110 correlating the Doppler shiftedsatellite signals from Doppler Block 108 by the output of Coder Block112 as shown in FIG. 9 while changing the estimated code phase. Inparticular, direct path correlation function 226 shows the shape of thecorrelation function that would result from adjusting the code phase, inthe absence of multipath interference, from about one C/A code chipwidth early, a delay or time offset of −1 chip, to about one chip widthlate, a delay or time offset of about +1 chip.

The triangular shape of direct path correlation function 226 isconventionally understood to result from the following circumstances.There will be almost no correlation between the signal received and theinternally generated code when the code phase offset is greater thanabout 1 to 1.5 chips in either direction. As the time offset is reducedfrom about 1 chip to about zero, in either direction, the correlationincreases to a maximum at zero offset. That is, when the code phase ofthe internally generated code is exactly equal (less biases, offsets andthe effects of filtering) to the code phase of the signal as receivedthe correlation peaks.

A delay-locked loop is conventionally used for tracking the expectedposition of peak 230, by using a pair of early and late correlators witha fixed offset or time delay there between, performing early and latecorrelations to surround or straddle peak 230.

As shown in FIG. 18, residual code phase errors resulting from multipathinterference can be detected, determined and/or corrected in accordancewith the present invention. In particular, satellite signals arereceived by GPS antenna 28 and processed by various components asdescribed above, as well as by Band Pass Filter 232, before beingcorrelated with a code replica produced by PN Code Generator 234. Thetime offset of the PN code produced by PN Code Generator 234 iscontrolled by the delay or offset of adjustable delay 236 driven bysystem clock 238.

The output of PN Code Generator 234, as offset, is applied to earlycorrelator 240 for correlation with the satellite signals as processedby Band Pass Filter 232. The output of PN Code Generator 234 is appliedthrough a pair of ½ chip delays 242 and 244 to late correlator 246, theother input of each of which is also provided by the output of Band PassFilter 232. As a result, the satellite signals are correlated at twopoints with a fixed 1 chip delay, or separation, there between. Thecorrelation functions are applied to detectors 248 which evaluates acharacteristic of the correlation function, such as the power. It shouldbe noted that other values or characteristics of the correlationfunction, typically a complex number including in-phase and quadraturephase components, can be used in place of power measurements includingamplitude measurements.

In accordance with conventional techniques, a delay-locked loop is usedfor code tracking by adjusting the time offset of adjustable delay 236so that the amplitude or power of the early and late correlationfunctions are maintained in a fixed relationship. In a preferredembodiment, the power of the early and late correlation functions aremaintained equal by Code Phase Error System 250 which adjusts the codephase time offset to maintain this relationship. Code tracking is thenperformed in that the actual time of arrival of the code from thesatellites is known to be within the one chip separation between theearly and late correlations while their powers remain equal.

Referring again to FIG. 17, when the delay-locked loop of FIG. 18 isshown to be properly tracking the code phase so that the early and latecorrelation amplitudes are equal, the relative magnitudes of early andlate correlations 252 and 254 are half of the magnitude of peak 230.That is, when the time phase offset is adjusted so that correlationamplitudes of equal value are tracked, these values symmetricallysurround, in time, the actual time of arrival of the signals shown inthe figure as prompt correlation 256. In other words, for a direct pathsignal, prompt correlation 256 is caused to occur midway between earlyand late correlations 252 and 254 so that prompt correlation 256 occursat zero time offset, i.e. at the actual time of arrival of the code. Asshown in FIG. 17, the amplitude of prompt correlation 256 is a relativeamplitude given a value of 1.0. The amplitudes of early and latecorrelations 252 and 254 have equal values of 0.5.

As shown in FIG. 18, to cause the prompt correlation to occur midwaybetween the early and late correlations, the 1 chip delay between earlyand late correlation is provided by a pair of ½ chip delays 242 and 244.The output of ½ chip delay 242 is applied to prompt correlator 240 toproduce prompt correlation 256, one half chip offset from earlycorrelator 240, for evaluation by detector 248. The input of ½ chipdelay 244 is provided by ½ chip delay 242 so the output of ½ chip delay244, applied to late correlator 246, is separated from the input toearly correlator 240, by one full chip offset. The outputs of detectors248 are then applied to complete the delay-locked loop.

Multipath distortion, if present, causes the prompt correlation to beoffset from the actual time of arrival of the satellite signals by anerror, described herein as the code phase residual error. The sign ofthe error between the prompt correlation and the actual time of arrival,either leading or lagging, has been determined to depend upon therelationship between the carrier phases of the direct and multipathsignals. When the difference in phase between the carrier phases of thedirect and multipath signals approaches 0°, as shown for example aslagging multipath correlation function 258, the direct and multipathsignals tend to reinforce, increasing the relative amplitude of thecorrelation products. When the difference in phase between the carrierphases of the direct and multipath signals approaches 180°, as shown forexample as leading multipath correlation function 260, the direct andmultipath signals tend to cancel, decreasing the relative amplitude ofthe correlation products.

More importantly, the relationship between the location of the actualtime of arrival, and the points of equal correlation amplitude, alsochanges. Without multipath, as discussed above, the points of equalmagnitude of early and late correlations separated by a fixed delay aresymmetrical about the correlation peak, that is, the actual time ofarrival, so that the point midway there between tracked as the punctualcorrelation is in fact the actual time of arrival of the code.

In accordance with the present invention, however, it has beendetermined that multipath interference, by reinforcement orcancellation, causes the points of equal amplitude early and latecorrelations to no longer be symmetrical about the correlation peak. Forexample, as can easily be seen by inspection of lagging multipathcorrelation function 258, the points of equal amplitude early and latecorrelation 252 and 254 are shifted to the right, that is to a positiveor lagging delay, with respect to the points of equal amplitude earlyand late correlation for direct path correlation function 226.

When the midway point in time offset between the early and latecorrelation is tracked, for lagging multipath correlation function 258,lagging prompt correlation 262 is offset in time from direct path promptcorrelation 256 by multipath reinforcement interference lag error 264.That is, lagging prompt correlation 262 is offset from the actual timeof arrival of the direct path signal by a positive or lagging delaytime. Similarly, when the midway point in time offset between the earlyand late correlation is tracked, for leading multipath correlationfunction 260, leading prompt correlation 266 is offset in time fromdirect path prompt correlation 256 by multipath cancellationinterference lead error 268. That is, multipath cancellationinterference lead error 268 is offset from the actual time of arrival ofthe direct path signal by a negative or leading lagging delay time.

In addition, the relationship between the early, prompt and latecorrelation product amplitudes are changed by multipath interference. Ascan be seen by inspection of lagging multipath correlation function 258,when the midway point in time offset between the early and latecorrelation is tracked, for lagging multipath correlation function 258,lagging prompt correlation 262 is greater in amplitude than direct pathprompt correlation 256. The amplitudes of early and late correlations252 and 254 for lagging multipath correlation function 258 are alsogreater than for direct path correlation function 226.

In particular, lagging prompt amplitude 270 is greater than 1.0 andequal early and late lagging correlation amplitudes 272 are greater than0.5. However, as can be seen by inspection and as demonstrated bysimulation, equal early and late lagging correlation amplitude 272 isgreater than one half of lagging prompt amplitude 270. Similarly,leading prompt amplitude 270 is less than 1.0 and equal early and lateleading correlation amplitudes 276 are less than 0.5. Further, equalearly and late leading correlation amplitude 276 is less than one halfof leading prompt amplitude 274.

In accordance with the present invention, these relationships are usedto determine the sign and magnitude of the offset errors multipathreinforcement interference lag error 264 and multipath cancellationinterference lead error 268. Code Phase Error System 250, shown in FIG.18, receives as inputs, the correlation amplitudes (or othercharacteristics as determined by detectors 248) of the correlationproducts from early correlator 240, prompt correlator 243 and latecorrelator 246.

If Code Phase Error System 250 determines that the amplitude of theprompt correlation performed midway between the early and latecorrelations is less than twice the amplitude of the equal early andlate correlations, then multipath reinforcement interference lag error264 exists. If Code Phase Error System 250 determines that the amplitudeof the prompt correlation performed midway between the early and latecorrelations is more than twice the amplitude of the early and latecorrelations, then multipath cancellation interference lead error 268exists.

If, however, Code Phase Error System 250 determines that the amplitudeof the prompt correlation performed midway between the early and latecorrelations is equal to twice the amplitude of the early and latecorrelations, then no multipath interference error exists.

That is, the existence of a multipath interference error may bedetected, and if detected the sign of the error may be determined bycomparison of the ratio of the amplitude of the prompt correlation tothe equal amplitudes of the early and late correlations offsetsymmetrically from the prompt correlation.

The relative magnitude of the multipath interference error may beestimated in several different manners. Depending upon the relativeamplitude of the multipath signal to the direct path signal, and thedifferences in carrier phase there between, an appropriate, empiricallydetermined scale factor, such as −0.5, multiplied by either the sum ofthe early and late correlation amplitudes divided by the amplitude ofthe punctual correlation, or by the square root of the sum of thesquares of the early and late correlation amplitudes divided by thesquare of the amplitude of the punctual correlation, will provide asuitable correction factor under most circumstances.

In other words, a computation correction to the pseudorange can be madeproportional to the amplitude of the (Early+Late)÷Punctual correlationsto reduce or eliminate the effect of multipath errors when the multipathdelay is less than about 1.5 PRN chips.

As shown in FIG. 18, there are three uses for residual multipath codephase error 278, which includes both the sign and estimated magnitude ofthe error. This error may simply be used in the rest of the receiver,shown as receiver processor 280, to computationally refine thepseudorange and therefore the position determination without changingthe operation of the delay-locked loop used for tracking the code phase.

Alternately, or in addition thereto, residual multipath code phase error278 may be applied to adjustable delay 236 which changes the time offsetof PN Code Generator 234 to control the offset of early correlator 240.The two ½ chip delays 242 and 244 maintain the separation from earlycorrelator 240 to late correlator 246 at one full chip width with promptcorrelator 243 centered there between. In this manner, prompt correlator243 may be made to more accurately track the time of arrival of thedirect path signal. In addition, separation control signal 281, producedfor example by Code Phase Error System 250, may be used to narrow orotherwise control the separation of the early and late correlations aswell as the symmetry around the prompt correlation to better track theactual time of arrival of the code.

Further, residual multipath code phase error 278 can be used inmultipath model 282 to enhance or provide a synthesized model of theinterfering multipath signal(s) used, for example, for multipathcancellation. Replica 284 produced by multipath model 282 may be appliedas a measurement input to error correcting feedback loop 286 whichreceives the signals from Band Pass Filter 232 as set point input 287 toproduce error signal 288 applied to multipath model 282. Error signal288 is used to control replica 284 to reduce any differences between thereplica and the signal received until the replica is an accuraterepresentation of the multipath signals. Multipath model 282 may thenprovide additional code phase correction 290, added by summer 292 toresidual multipath code phase error 278, for adjustment of PN CodeGenerator 234.

As noted above with respect to separation control signal 281, it may bedesirable under certain circumstances to reduce the separation, or timeoffset, between early correlator 240 and late correlator 246 forimproved tracking. This technique of reducing the separation has alsobeen used in attempts to minimize residual error from multipathinterference by straddling the peak of the correlation function. Itshould be noted from inspection of FIG. 17 that the peak of thecorrelation function is easiest to select by straddling direct pathcorrelation function 226 because a relatively steep slope occurs on bothsides of peak 230, making the peak easier to distinguish.

As the separation between the early and late correlations is reduced inthe presence of multipath, however, at least one of the sides of thepeak becomes less steep. For example, the slope of the lagging edge oflagging multipath correlation function 258 is substantially less steepthan the leading edge thereof. Similarly, the slope of the leading edgeof leading multipath correlation function 260 is also less steep thanthe slope of its lagging edge. As the slope becomes less steep in theneighborhood of the peak and the prompt correlation, it becomes moredifficult to detect or straddle the peak, particularly in the presenceof noise. In accordance with one embodiment of the present invention,the sign and magnitude of the error may first be determined in order toreduce multipath effects before reducing the separation for trackingpurposes.

It should also be noted from FIG. 17 that two correlation peaks areproduced by the cancellation interference. Although it might be possibleto track the wrong peak by accident, it is only necessary to determineif another, earlier and perhaps larger correlation peak exists within asmall separation to cause the delay-locked loop to track the correctpeak.

In order to provide an accurate assessment of the multipath error, thebaseline due to noise must be removed. Referring now to FIG. 3, thepresent invention permits the convenient and accurate assessment of thebaseline due to noise as a result of the use of a relatively largenumber of correlators, such as Exclusive NOR gate correlators 74. Inparticular, a correlator 74 at a substantial earlier correlation time ordelay than the prompt tap can be used to assess the baseline due tonoise. In this way, the noise can be determined without interference byany correlation with the desired signal.

FIG. 19 is a block diagram schematic of GPS receiver 310 constructed inaccordance with another embodiment of the present invention.Conventional omni-directional, half-hemispherical GPS antenna 312receives PRN encoded signals from a plurality of GPS transmitters, notshown. The signals as received may, or may not, include multipathsignals which if present are to be canceled by the operation of GPSreceiver 310 in accordance with the present invention. In the particularimplementation of GPS receiver 310 shown in FIG. 19, the signals arereceived, downconverted, bandpass filtered and converted to digitalsignals for further processing, in receiver front end 314. Thisparticular implementation of front end 314 works particularly well inthe receiver of the present invention, but many other front endconfigurations may well be used with the present invention.

In particular, within front end 314, the signals received byomni-directional GPS antenna 312 are applied to RF receiver 316 afterwhich they are downconverted in mixer 318 by being mixed with a knownlocal oscillator (LO) signal produced by LO frequency synthesizer 320.Thereafter, the downconverted signals are processed in intermediatefrequency processor 322 and filtered in band pass filter (BPF) 324. Thedownconverted and bandpass filtered received signals are finallyconverted to digital signals in analog to digital converter (ADC) 326 toproduce a digitized version 328 of the signals as received. The doublelines used in FIG. 19 for digitized version 328 represent that thesignal information included therein has a complex value. It should alsobe noted that known direct conversion techniques could also be used.

ADC 326 is controlled by Sample Clock 321 from frequency synthesizer 320at a particular rate, typically faster than the chip rate at which thesignals transmitted by the GPS receivers are encoded. In this particularembodiment, sample clock 321 runs 32 times faster than the chip rate andis applied to ADC 326 so that information related to each {fraction(1/32)}nd of each chip may be determined.

Digitized version 328 of the signals as received is applied to CarrierTracking Loop 330 which may be a conventional carrier tracking loopmodified by the addition of cancellation subtractor 332 as well as theprovision for tracking loop raw measurement signal 334 at the output ofphase rotator 336. The operation of Carrier Tracking Loop 330 will bedescribed below in greater detail after the details of operation ofnon-encoded replica signal synthesizer 338.

Replica signal synthesizer 338 provides Phase Tracking Error 340 tocancellation subtractor 332 in Carrier Tracking Loop 330 forcancellation of multipath signals in cancellation subtractor 332. Asshown in FIG. 19, the components included within replica signalsynthesizer 338 are somewhat arbitrarily included in FIG. 19 in thatmany such components, such as PRN generator 342, Coder NCO 344 and othercomponents may also be present for use in other parts of GPS receiver310. For ease in description of the current invention, the operation ofsuch components within replica signal synthesizer 338 will be describedherein.

The primary operation of replica signal synthesizer 338 is performed byFinite Impulse Response (FIR) Filter 346 which includes summer 348 andBinary Shift Register 350. In the preferred embodiment shown in FIG. 19,a 48 channel summer 348 and a 48 channel Binary Shift Register 350 wereselected in order to evaluate about 1.5 C/A code chips widths of signalat one time for multipath cancellation. That is, Sample Clock 321operates at 32 times the C/A code chip width so that 48 such sampleswould capture about 1.5 C/A code chips. Inaccuracies of greater thanabout one or one and one half chip widths, resulting for example frommultipath, are conveniently handled elsewhere in the GPS receiver using,for example, conventional techniques.

A series of 48 switches 352, one in each channel between Binary ShiftRegister 350 and Summer 348, are controlled by the channels of BinaryShift Register 350 to apply a series of 48 channel error signals 354, tobe described below in greater detail, to a corresponding channel ofSummer 348.

During a progression of 48 pulses from Sample Clock 321, whichrepresents on the order of 1.5 chips of encoded PRN modulation indigitized version 328 of the signals as received, the satellite specificPRN code 343 for the satellite of interest is applied to Binary ShiftRegister 350. Satellite specific PRN code 343 may be produced in agenerally conventional manner, as shown for example in coder sub-system337, by clocking the output of satellite specific Code NumericallyControlled Oscillator (NCO) 344 into conventional PRN Code Generator342. Satellite specific PRN code 343 is applied to Binary Shift Register350 under the control of Sample Clock 321 so that the leading edge ofeach PRN code pulse is applied to stage 1 of Binary Shift Register 350while the remaining stages contain the remainder of the 1.5 chip samplediscussed above.

Punctual PRN code 345, derived from the application of satellitespecific PRN code 343 to Binary Shift Register 350 by computing fromstage 1 or perhaps stage 2, is applied to Carrier Tracking Loop 330 toproduce in phase or I component 372, as will be described below ingreater detail with respect to Carrier Tracking Loop 330. Codersub-system 337 also produces Code Tracking Error Signal 341 from replicasignal synthesizer 338, as will be described below in greater detail.

The 48 channel error signals 354 are each derived from complex errorsignal 356 by correlating with the corresponding output from BinaryShift Register 350 and are individually weighted and integrated, inchannel gain/signals conditioning systems 355, in a manner tending toreduce the magnitude of complex error signal 356 by adjustingMeasurement Signal 364 to better approximate Set point signal 362, thatis, to better match and therefore cancel the signals as received,including multipath errors, if any. In the preferred embodiment, asshown in FIG. 19, a complex form of the Least Mean Square, or LMS,approximation algorithm is used although many other known approximationtechniques could be used. The error tracking loop serves to conditionand weight complex error signal 356 to force measurement signal 364 toequal Set point signal 362.

Set point signal 362 is applied to tracking loop subtractor 360 as theSet point signal to be maintained and is derived from digitized version328 of the signals as received while measurement signal 364 is theoutput of Summer 348 in replica signal synthesizer 338 representing thereplica of the signals as received. A zero value for complex errorsignal 356 indicates that measurement signal 364 must have been equal toSet point signal 362 from which it was subtracted.

Set point signal 362 is derived from digitized version 328 of thesignals as received after phase rotation by phase rotator 336 in CarrierTracking Loop 330 and subsequent demodulation in Data Bit Demodulatormultiplier 370 by being multiplied by an estimate, or measured value, ofthe 50 bits per second (bps) navigation modulation applied to the C/Asignal of each GPS satellite transmitter, shown in FIG. 19 as Nav databits 368. The removal of the effect of the navigation modulation isnecessary so that the C/A code modulation may be tracked directly. Thebi-phase navigation message modulation, at 50 bps, may be removed asshown in FIG. 19 by stripping the modulation from raw measurement signal334 in data bit multiplier 370 or by mod-2 adding the modulation tosatellite specific PRN code 343 as will be described below in greaterdetail with reference to FIG. 20.

Referring now again to FIG. 19, during operation, the data message andtherefore Nav data bits 368, may already be known. Since this datamessage may normally be expected to not change very quickly, the databits may be stripped from raw measurement signal 334 by multiplying Navdata bits 368 with raw measurement signal 334 in data bit multiplier370. Even if the full data message is not exactly known, portions of themessage may be known or assumed because the message changes very slowlycompared to the bit rates of the signals being processed. The positionwithin the navigation message may be known and used, such as the headeror protocol information indicating the type of information to follow,that is, the header for the time and date information. It is onlynecessary to know enough about the data message to properly model themultipath signals for cancellation.

Referring now also to FIG. 20, if the data bit message is not currentlyknown, it may be estimated by demodulation as shown or in any otherconvenient fashion. For example, the In Phase or I component 372 of theCostas Loop demodulation associated with the punctual or on-timecorrelation in Carrier Tracking Loop 330 in response to punctual PRNcode 345, may be integrated over each 20 ms duration of a 50 bps navdata bit to indicate the polarity, and therefore the binary amplitude of1 or 0, for that data bit. In accordance with the embodiment of thepresent invention shown in FIG. 20, in phase or I component 372 isapplied to 20 ms Integrator and Digitizer 374, and synchronized with theGPS C/A code as received. This synchronization may be accomplished byclocking the integration in 20 ms Integrator and Digitizer 374 with databit timing signal 376, derived from PRN Code Generator 342 in coder 337,or in any other convenient fashion.

In the preferred embodiment, Integrators 373 (shown in FIG. 20) includedin both the I and Q signal paths in the Costas Loop in Carrier TrackingLoop 330 already provide integration of at least 20 ms, so that furtherintegration in 20 ms Integrator and Digitizer 374 is not required. Ifthe integration provided by Integrators 373 is less than 20 ms, a 20 msintegration time is provided by 20 ms Integrator and Digitizer 374.

The output of 20 ms Integrator and Digitizer 374 is in the form ofDemodulated Data Bits 378. The time ambiguity as to which 1 msecrepetition of the C/A code modulation marks the start of the data bitmay be resolved in any one of the many conventional techniques known.

However, this estimate of the data bit information provided by 20 msIntegrator and Digitizer 374 is not available until the end of the 20ms. bit duration of the 50 bps Nav Data modulation. This 20 ms. lag isacceptable for many replication synthesizers, such as the complex LMSfeedback adaptation used in replica signal synthesizer 338. An elegantbut simple solution of this problem of the lag of the estimate forDemodulated Data Bits 378 is to use each of the two possible values forNav data bits 368 in one of a pair of replica signal synthesizers andthen select the synthesizer outputs from the synthesizer determined, atthe end of the 20 ms. period, that happened to have used the correct bitvalue.

As shown in FIG. 20, in one implementation of this approach, rawmeasurement signal 334 from Carrier Tracking Loop 330, and satellitespecific PRN code 343, are both applied in parallel, both to first FIR346 a as well as to second FIR 346 b. As an alternative to stripping theNavigation Message Data Bits from raw measurement signal 334 to form Setpoint signal 362, the data bit is mod-2 added to satellite specific PRNcode 343, to represent the 180° possible phase shift due to theNavigation Message Modulation, in inverter 347 before the code isapplied to second FIR 346 b.

In particular, a predicted data bit value of bit=0 is accomplished byapplying satellite specific PRN code 343 directly to first Binary ShiftRegister 350 a in first FIR 346 a. First replica signal synthesizer 338a includes first FIR 346 a which uses complex LMS Tracking Algorithm 339a to synthesize measurement signal 364 in Summer 348 a in response tofirst Binary Shift Register 350 a. A predicted data bit value of bit=0is applied to first Binary Shift Register 350 a in first FIR 346 a byapplying satellite specific PRN code 343 directly to first Binary ShiftRegister 350 a. The outputs of complex LMS Tracking Algorithm 339 ainclude h_(1a), and h_(2a) which represent the weightings of the firsttwo time segments of first FIR 346 a.

A predicted data bit value of bit=1 is applied to second Binary ShiftRegister 350 b in second FIR 346 b by applying satellite specific PRNcode 343 through inverter 347 to second Binary Shift Register 350 b. FIR346 b uses complex LMS Tracking Algorithm 339 b to form to synthesizemeasurement signal 364 b in summer 338 b of second FIR 346 b in responseto second Binary Shift Register 350 b. The outputs of complex LMSTracking Algorithm 339 b include h_(1b) and h_(2b) which represent theweightings of the first two time segments of second FIR 346 b.

In order to determine which of the predicted Nav Data Bit Modulationvalues, 1 or 0, was correct, at the end of a 20 ms. integration time,the actual value of the Nav Data Message Modulation is applied to bitcomparator and data switch 382 by Demodulated Data Bit 378 from 20 msIntegrator and Digitizer 374, together with h_(1a) and h_(2a) from firstFIR 346 a and h_(1b) and h_(2b) from second FIR 346. If the actual databit had a data bit value of bit=0, i.e. no phase shift, then bitcomparator and switch 382 applies h_(1a) and h_(2a) from first FIR 346 aare applied as h₁ and h₂ to coder sub-system 337. In addition, h_(1b) toh48 b in second FIR 346 b are replaced by h_(1a) to h48 a from first FIR346 a. If however, Demodulated Data Bit 378 indicates a data bit valueof bit=1, then bit comparator and switch 382 applies h_(1b) and h_(2b)from second FIR 346 b as h₁ and h₂ to coder sub-system 337. In addition,h_(1a) to h48 a in first FIR 346 a are replaced by h_(1b) to h48 b fromsecond FIR 346 b. In this manner, the system is updated every 20 ms evenif the Nav Data Bit Modulation is not known a priori.

With reference again in detail to FIG. 19, the use of h₁ and h₂ in codersub-system 337 will now be described in greater detail. As noted above,these two values represent the weightings of the first two time periodsused in the successful replication of the signal as received, includingmultipath effects. h₁ and h₂ are combined in adder 384 for conversion byArcTangent converter 386 into Phase Tracking Error 340 which is thenapplied by coder sub-system 337 to Carrier Tracking Loop 330.

In addition, the magnitudes of h₁ and h₂ are squared in squarers (oralternatively absolute values) 388 for subtraction by subtractor 390 toproduce Code Tracking Error Signal 41 for use by Code Loop Filter 392which drives coder NCO 344. Estimated Carrier Phase 379 is produced byCarrier Tracking Loop 330 and may be used for dynamic aiding, especiallyfor a moving platform such as an automobile, by being scaled to the PRNchip rate in Divide by 1540 Scaler 394 for combination with the outputof Code Loop Filter 392 in adder 396 before application to Coder NCO 344which drives PRN Code Generator 342 and produces Estimated Code Phase398.

Estimated Carrier Phase 379 and Estimated Code Phase 398 are used in aconventional GPS data processor, such as Processor 29 shown in FIG. 19,to derive the required position information.

Referring now again to data bit multiplier 370 in FIG. 19, one advantageof stripping the Navigation Data Bit Modulation from raw measurementsignal 334 to form Set point signal 362 is related to the need toreplicate Binary Shift Register 350 when the Nav Data Modulation is notknown. An alternate approach is to add the Navigation Data BitModulation to measurement signal 364 by, for example, appropriatelyinverting satellite specific PRN code 343 as applied to FIR 346. Thatis, when both possible Data Bit Modulation values of the NavigationMessage must be tested, stripping Nav data bits 368 from (FIR) Filter346 in data bit multiplier 370 of FIR 346, as shown in FIG. 19, permitsreplication of parallel FIRs 346 driven by a single Binary ShiftRegister 350. This configuration is shown below in FIG. 21.

As shown in FIG. 20, however, when testing for the Navigation MessageData in a configuration in which the two possible Navigation Messagebits are created by inverting to one of a pair of FIRs 346, duplicateBinary Shift Registers 350 a and 350 b are required. Stripping of theNavigation Message before application to FIR 346 therefore provides theadvantage of reducing the component count in a parallel system by BinaryShift Register 350 b.

Referring now to FIG. 21, digitized version 328 of the signals asreceived are applied to Carrier Tracking Loop 330 for phase rotation byphase rotator 336 to form raw measurement signal 334 which is strippedof Nav data bits 368 by data bit multiplier 370 in the same manner as inFIG. 19. Raw measurement signal 334 is then applied to first replicasignal synthesizer 338 a to represent a Nav Data Bit modulation ofbit=0. Resultant set point signal 362 represents a Nav Data Bitmodulation of bit=1 for application to second replica signal synthesizer338 b. It is important to notice that contrary to the configurationshown in FIG. 20, both first FIR 346 a and second FIR 346 b are drivenby a single Binary Shift Register 350, the outputs of which are appliedin parallel to both filters. Complex LMS Tracking Algorithm 339 areceives the prompt code signal satellite specific PRN code 343 viaBinary Shift Register 350 and applies punctual PRN code 345 to CarrierTracking Loop 330.

The remaining outputs of the error tracking loops are h_(1a) and h_(2a)from first FIR 346 a and h_(1b) and h_(2b) from second FIR 346 b whichare compared with Demodulated Data Bit 378 from 20 ms Integrator andDigitizer 374 in bit comparator and switch 382 to determine which of thefilter outputs is applied to coder sub-system 37 as h₁ and h₂. Theoperation of the embodiment of FIG. 21 is therefore much like that ofFIG. 20 except that the Nav Data Bit Modulation is stripped from rawmeasurement signal 334 rather than added to satellite specific PRN code343. As noted above and apparent from FIG. 21, one of the beneficialresults of this configuration is the use of a single Binary ShiftRegister 350 rather than first Binary Shift Register 350 a and secondBinary Shift Register 350 b as required in the configuration shown inFIG. 20.

Referring now to the operation of the embodiments shown in FIGS. 19-21,the use of Nav Data Bit Modulation derived from the signals as received,which may include substantial multipath errors, does not substantiallydegrade the operation of a typical receiver. In particular, a typicalreceiver may be assumed to operate, for example, at a signal level of 38dB-Hz, E_(b)/N₀=21 dB at the 50 bps data rate of the Navigation DataBits where E_(b) represents the energy per bit and N₀ represents thewatts per hertz. The bit error rate would then be 10⁻³ at approximatelyE_(b)/N₀=7 dB. Thus the punctual correlation can be severely degraded bythe multipath without significantly introducing errors into the data bitestimates, as verified by simulations. In other words, the relativegreater magnitude of the signal and its error rate over the magnitudeand estimate of the Navigation Data Bits means that multipath errors inthe Navigation Data Bits don't significantly effect the processing ofthe receiver signals.

In order to mathematically analyze the operation of the cancellationapproach of the present invention, the received signal, with K multipathcomponents, can be modeled as $\begin{matrix}{{s(t)} = {{{b(t)}{\sum\limits_{k = 0}^{K}\quad {a_{k}^{{j\varphi}_{k}}{{PN}\left( {t - \tau_{k}} \right)}}}} = {{b(t)}{\sum\limits_{k = 0}^{K}\quad {\alpha_{k}{{PN}\left( {t - \tau_{k}} \right)}}}}}} & (1)\end{matrix}$

using a complex representation of magnitude and phase on the carrier.For each multipath component, τ is the delay in PRN chips, a is themagnitude, and φ is the carrier phase. For mathematical convenience, themagnitude and phase can be combined into the single complex value α. Thedirect component corresponds to α₀, and its time of arrival and phaseare the desired measurements for purposes of navigation. Only multipathcomponents delayed by less than roughly one PRN chip are of concern inEq(1), since the PRN code is uncorrelated for longer multipath delays.

Injecting the known PRN code into a binary shift register as shown inFIG. 19, the general estimate $\begin{matrix}{{{est}(t)} = {\sum\limits_{m = 1}^{M}\quad {h_{m}{{PN}\left( {t - \tau - {mT}} \right)}}}} & (2)\end{matrix}$

is synthesized, where T denotes a design time spacing in PRN chips andthe h_(m) values are complex values to be determined. A plot of h_(m)versus mT is the multipath profile estimate in the receiver, ideally,would match the actual profile. The h_(m) values may be called the “tapweights”, and T is the tap spacing. The shift register in FIG. 19 shiftsevery T.

In order to accurately model the input signal as distorted by multipath,it is necessary to make τ in Eq(2) approximate τ₀ in Eq(1). The receiverprocessing adjusts τ, and the h_(m) values, to minimize the mean squarevalue of

ε=b _(e)(t)[s(t)+n(t)]−est(t)  (3)

where b_(c)(t) is an estimate of the data bits. As discussed above, thedata bits can be effectively stripped off. Then, a straightforwardapproach to adjusting the h_(m) is the well-known complex LMS algorithmto minimize the mean square error of a weighted sum compared to adesired result. In Eq(3), s(t) is the desired result, and ε is thecomplex error. Applied to the present task, the complex LMS algorithm isdescribed by the feedback adaption

Δh _(m) =gPN*(t-mT)ε  (4)

which adjusts each h_(m) value to minimize the mean square error. Thegain constant g sets the time constant of the adaption. A small greduces the error due to noise and ensures stability of the feedbackloops. Eq(4) shows a complex conjugate is to be taken of the PRN code ingeneral, but this is unnecessary in the present application where PRN(t)is real (±1 values).

The value of τ can be estimated by determining the earliest significantvalue of h_(m) when the receiver is tracking conventionally either bydifferencing early and late correlation powers (delay-lock tracking) orby forming the dot product between an early-late correlation and apunctual correlation (dot-product tracking). This approach views thecomputation of the multipath profile estimate as a providing acorrection to conventional PRN tracking.

In accordance with the present invention, an alternate and preferableapproach to estimate a is now described. To begin, assume there is nomultipath, only the direct component. Ideally, only one h_(m) would benon-zero in the multipath profile estimate; however, because of theeffect of the finite receiver bandwidth, the multipath profile estimateactually has a non-zero width. Then, a restoring force for adjusting taucan be obtained by differencing two adjacent h_(m) values, e.g.,

Tracking Restoring Force=|h₁|²−|h₂|²  (5)

In effect, τ is adjusted by this method of tracking towards a trackingnull so that the direct component falls midway between the earliest twoadjacent taps of the multipath profile estimate. (Note, it may bepreferable to displace the two adjacent taps used in Eq(5) to a littlelater in the multipath profile estimate.) Then, a tracking loop for τcan be closed to force the restoring force of Eq(5) to the trackingnull.

Now suppose that a multipath component suddenly appears. The LMSfeedback adaption to estimate the multipath profile causes other valuesof h_(m) for m>2 to develop non-zero values, but, ideally, h₁ and h₂ arenot affected. Thus, ideally, τ continues to be tracked without asignificant error.

The carrier phase of the direct component is contained in the complexvalues of h₁ and h₂ when tracking τ as described above. Since the directcomponent falls between these two taps, an estimate of carrier phase isgiven by the phase of h₁+h₂. Ideally, when a multipath componentsuddenly appears, the estimate of carrier phase of the direct componentis affected only slightly.

A practical concern of carrier tracking is being able to track duringvehicle dynamics. For this reason, FIG. 19 shows the usual punctualcorrelation to generate I and Q components that are used to compute theerror for standard Costas loop tracking of the dynamics. The carrierphase determined from h₁ and h₂ for the direct component is subtractedfrom the Costas error so the Costas loop is tracking the estimated phaseof the direct component.

The estimated carrier phase is scaled by 1540, in Divide by 1540 Scaler394, which represents the ratio of carrier frequency to PRN chip rate,and injected into the code tracking in Coder NCO 344 to remove theeffect of dynamics from the code loop.

Referring now to FIG. 22, the operation of an alternate embodiment ofthe present invention is shown in which multipath errors at delaysgreater than about 1.5 C/A code chips can be detected and corrected.This technique for the correction of long delay, non-interferingmultipath signal errors (i.e. delay greater than about 1.5 chips) may beused in combination with techniques for short delay, constructive ordestructively interfering multipath signal errors (i.e. delay less thanabout 1.5 chips) such as those shown in FIGS. 17 through 18 and FIGS.19-21, or may be used alone.

In an urban environment, or any other in which there are substantialpotential signal blocking and reflecting objects, GPS and other spreadspectrum receivers occasionally lock onto and track a reflected ormultipath signal. Although tracking of a multipath signal may begin whenthe direct path signal from the transmitter is blocked, tracking of themultipath signal will often continue even when the direct path signallater becomes available, thereby losing potentially valuable navigationinformation.

This multipath problem may also occur in sites selected for differentialGPS transmitters as a result of reflections, for example from a blackasphalt parking lot adjacent the transmitter, as the angle of theincoming signal changes because of satellite motion.

If the direct path signal thereafter becomes available, it would beadvantageous to force the receiver to lock onto the direct path signaland ignore the reflected signal that had been tracked. To do this,direct path and multipath reflection signals must easily bedistinguished from each other. In accordance with the operation of theembodiment depicted in FIG. 22, the greater than conventional number ofcorrelators available to track the incoming signals for each satellitein order to provide fast reacquisition are advantageously used to verifythat the signal being tracked is in fact the direct signal rather than alater arriving multipath signal. If an un-tracked direct path signal, oreven a shorter path multipath reflection signal, is detected, thetracking is immediately moved to the better signal.

During satellite tracking, in addition to performing early, prompt andlate correlations to maintain tracking accuracy, the present inventionutilizes a plurality of progressively earlier correlations to detect thepresence of a satellite signal substantially earlier than the signalcurrently being tracked as the prompt signal. When an earlier signal isdetected it is assumed to be a more valuable signal, such as the directpath signal or at least a shorter path multipath reflection signal,especially when the magnitude of the earlier correlation is larger thanthe magnitude of the prompt correlation for the signal being tracked.When an earlier, more valuable signal is detected, the code delay orcode phase is adjusted so that the earlier signal is tracked as the newprompt correlation signal. A related phenomenon has been discovered,related to the rate of change of drift of a reflected path signaltowards, or away from, the direct path signal. For example, in areceiver located above a black asphalt parking lot, the reflected pathsignal is later than the direct path signal but the delay is notconstant. As the angle of incidence of the signals received from thesatellite changes, the delay changes. The rate of change of the delay,that is, the speed of progression, provides substantial informationabout the reflector including its physical qualities such as angle anddistance.

In addition to using this information for other purposes, the speed ofprogression may be helpful in those cases in which the difference inamplitudes of the direct and reflected paths cannot be used todistinguish between the direct and reflected signals. That is, thereflected path signal will change in time of receipt from the desiredsignal and will also change in a manner distinguishable from direct pathsignals. Many characteristics of the desired, direct path signals areknown from the ephemerides even when the exact time of arrival is notyet known. The rate of progression of a reflected signal will differfrom that expected from progression of the direct path signal caused bysatellite motion and may therefore be used to identify the direct pathsignal. In some situations, particularly in fixed locations such asdifferential GPS transmitting stations, the receiver may be calibratedfor known reflectors, such as the black asphalt parking lots describedabove.

In other situations, such as in a moving vehicle in an urban environmentin which there are rapid changes of reflectors and the direct path maybe blocked several times, the information from a strong multipath signalmay be corrected on the basis of the rate of progression, perhaps byseparately tracking the reflected path signal, so that the “deadreckoning” or modeling of the direct path signal may be improved bytracking the reflected path in the interims when the direct path isblocked.

In operation, as shown in FIG. 22 and as previously described withregard to FIG. 11, each 11 ½ chip sample or segment is Doppler rotatedto provide a satellite specific sample for each SV being tracked.Segment #1 is first processed in SatTRAK channel 38 for SV 1 with aDoppler rotation specific for that SV at that time and then processed inSatTRAK channels 40, 42 and 44 SV's 2-4 (and so on for all 11 SV's) byDoppler rotating the segment for each SV in each channel. Each Dopplerrotated version of Segment #1 is then, in turn, delayed by each of 22satellite specific code delays to determine the correlation magnitudesfor each of the 22 delay theories for that SV.

Thereafter, the 11 ½ chip samples of each of the remaining 185 segmentsin each ms code repetition period are processed in the same manner. Theresults of the correlation for each delay for each of the 12 SVs areaccumulated in a matrix of correlation magnitudes for SVs as a functionof tap number or delay. For example, the accumulation of correlationamplitudes for correlations of the signals from SV #1 in SatTRAK channel38 is shown in FIG. 22 in Row 1 for time T0. The magnitudes are shown onan arbitrary scale. It is convenient to use a magnitude representing thepower of the correlation product, rather than the magnitudes of theindividual I and Q quadrature phase signals which may be used in thetracking mode. The I and Q correlation products may be thereafterconverted to power in accordance with the conventional conversionformula in which the power is the square root of the sum of the squaresof I and Q or power measurements and peak detection may be accomplishedwithin each channel. An alternate approach is described below withregard to FIG. 23 in which a fast reacquisition channel, which alreadyincludes power conversion and peak detection, may be used as a separatecode phase verification channel.

In either event, the prompt correlation delay would be normally adjustedso that the results of the prompt correlation are accumulated in tapcolumn #2 (or at some other fixed location such as the center of thedelay line).

In the example shown for SV #1, the early correlation is accumulated incolumn #1 which shows a magnitude of 4 for the 186 segments representinga full repetition of the C/A during 1 ms. The prompt and latecorrelation accumulations as shown in columns #2 and #3 with magnitudesof 8 and 4, respectively. Similarly, the accumulated magnitudes for theearly, prompt and late correlations in SatTRAK channels 40, 42 and 44are shown in columns 1, 2 and 3 of rows R2, R3 and R4 with magnitudes of6, 12 and 6 for SV #2; 4, 8 and 4 for SV #3 and 2, 4 and 2 for SV #4.For the purpose of illustration, a multipath reflection of the signalfrom SV #1 is indicated in SatTRAK channel 38 centered at column #17with magnitudes of 2, 4 and 2 while a multipath signal from SV #4 isindicated in SatTRAK channel 44.

In this configuration in which the early, prompt and late correlationsare performed with delays or tap weights of 1, 2 and 3 respectively, theremaining correlations with tap weights greater than 3 may besuperfluous during the tracking mode. In order to save battery energy orincrease the speed of multiplexing, these correlations may be turnedoff.

In accordance with the present invention, the early, prompt and latecorrelations may also be processed at the greatest delays, at tapweights at or near 20, 21 and 22. At Row 1, time t₁, the correlationmagnitudes for SV #1 in SatTRAK channel 38 are shown with the promptcorrelation being performed at column #21. If, as is shown, the promptcorrelation has been locked in error onto a multipath reflection, theSatTRAK channel 38 is inadvertently tracking a multipath reflectionrather than the desired direct path signal. The direct path signal ifvisible will reach the receiver along a shorter path and therefore at anearlier time, that is, at an earlier tap or delay number. As an example,the correlation magnitudes accumulated for SV #1 in SatTRAK channel 38in columns 6, 7 and 8 shown magnitudes of 6, 12 and 6 indicating thatthe direct path signal is present at a time corresponding to tap ordelay #7. As shown in FIG. 17, the correlation shape for a direct pathsignal, such as direct path correlation function 226, is expected to bean equilateral triangle.

When the accumulated magnitudes in SatTRAK channel 38 are analyzed, thedirect path signal at tap #7 is detected and thereafter the correctprompt correlation is made at this time. This may be accomplished byshifting the delays of the taps so that the delay associated with tap #7is thereafter present at tap #21. Thereafter, any other earlier signalsoccurring and accumulated for tap weights #1 through #19 may again beused to look for and detect a direct path signal if the currentlyselected prompt delay is inaccurate. Similarly, the early, prompt andlate correlation accumulations for SVs #2, #3 and #4 are shown in Rows2-4 at time t₁.

With regard to SatTRAK channel 38, the detection of the direct signalpath at tap #7 rather than tap #21 indicates that the multipath signalpath length was 15 ½ chips longer than the direct path or about 2½ mileslonger, assuming about 6 ½ chips represents one mile.

In accordance with another aspect of the present invention, it may beadvantageous to continue to track the multipath signal to obtainadditional information for the correction of multipath interference whenthe multipath signal path length is only about 1.5 ½ chips (or less)greater than the direct path. Similarly, tracking the multipath signalmay be useful in order to model the direct path signal if the directpath signal is temporarily obscured. In particular, obscuration of thedirect path signal may lead to locking onto the multipath signal so thatwhen an earlier direct path signal is detected, it is reasonable toassume that the direct path signal may later be obscured again.

In particular, as shown for SatTRAK channel 38 in row 1, t₂, the directpath signal may be maintained at tap #7 where detected and the progressof the multipath reflection monitored. In the short run, the change inpath length due to vehicular motion may well be substantially greaterthan the change in path length due to satellite motion. In either event,however, if the multipath signal path length grows with respect to thedirect path length, it is likely that the multipath signal will notcause additional tracking difficulties. If however, as shown, thedifference in path length is decreasing, the magnitude of thecorrelations of the multipath signal may well increase.

At time t₂, the multipath signal path length has decreased to be onlyabout 2 miles longer than the path length of the direct path so that themultipath correlations are accumulated in columns about 12 ½ chip delaysfrom the corresponding magnitudes of the direct path correlations. Inorder to track both the multipath and direct path signals within thesame 22 tap delay line, the direct path signal must be correlatedbetween taps 2 and 10. In the example shown, the direct path remains attap 17 so that the multipath signal can be tracked at tap #19.

At a later time shown as time t₃, the additional path length for themultipath signal has been reduced to about 1.5 miles which isrepresented by only 9 ½ chip delays. When the path length difference isless than or equal to half of the number of taps, it may be convenientto relocate the prompt correlation for the direct path signal to themidpoint of the row, that is, to tap #11. The multipath signal at adifferential path length of about 9 ½ chip delays is then accumulated attap #20.

At a still later time shown as time t₄, the path length differential hasbeen reduced to about 6 ½ delays and the multipath signal correlation istherefore accumulated at tap #17. As an example, the magnitude of thestrongest multipath correlation is shown as 10, a substantial increaseover the magnitude at the larger path length differential. This increaseis consistent with the changes in multipath reflection which occur whenthe vehicle containing the GPS receiver moves toward a multipathreflector, such as a building or mountain.

Similarly, at a still later time t₅, the path length differential hasbeen reduced to about one half mile so that the multipath signalcorrelation magnitudes are accumulated in taps #13, #14 and #15. At thisstage, the multipath correlation is within about 1.5 ½ chip delays fromthe direct path correlation accumulated at taps #10, #11 and #12. Asnoted above with respect to FIG. 17, when the path length differentialis within about 1.5 ½ chip delays, the correlation products mayconstructively or destructively interfere, making it more difficult toaccurately track the direct path signal.

However, as may be seen from an inspection of FIG. 22, the progressivechange in the path length differential may be modelled as a function oftime. Although shown as a somewhat linear progression, the actualprogression may take any form depending upon the location and type ofreflector as well as the relative path and changes of direction of thereceiver, all of which may be modeled to provide a relatively accuraterepresentation of the multipath signal during the period of interferencewith the direct path signal. The correlation products modelled for themultipath signal may then be subtracted from the direct pathcorrelation, or otherwise compensated for, in order to more accuratelytrack the direct path.

In addition, as shown in FIG. 17, the shape of the distorted correlationcaused by the multipath interference may be taken into account in thecorrection or compensation of the direct path correlation for trackingpurposes.

Further, referring now specifically to time t₆, after the path lengthdifferential has reached a minimum (which may be zero as the multipathsignal disappears if the vehicle approaches the reflector), themultipath path length differential may begin to increase again. It maybe advantageous to track the multipath signal, while the differentialpath length is decreasing as noted above, in order to compensate formultipath interference. In addition, it may be advantageous to track amultipath correlation, or at least the multipath signal with thegreatest signal magnitude, whether the path length differential isincreasing or decreasing, in order to model the direct path signalduring periods of obscuration.

At time t₆, the path length differential has increased to about 1 mile,but the direct path signal has been obscured by the environment, thatis, by a building, by foliage, by a hill or the like. By tracking theprogress of a major multipath signal, if available, including changes ofthe direction of progression of the path length differential, anaccurate model of the direct path may be maintain during brief, or notso brief, periods when the direct path signal is obscured. The model ofthe direct path signal may be maintained in any convenient manner, suchas in a matrix of modelled correlation products.

Referring now to FIG. 23, the code verification function described abovemay be configured in a different fashion to take advantage of some ofthe functions of the fast reacquisition embodiment discussed above withrespect to FIG. 3. In one embodiment of the present invention, eachsatellite tracking channel may be operated in either a satellitetracking mode, in which quadrature correlation of the I and Q signalsfrom a satellite are performed at each of 22 tap delays to track thatSV, or in a fast reacquisition mode in which the correlation power ateach of 22 tap delays are determined and the peak power is selected inthe same manner as used during reacquisition.

In the particular embodiment of the fast reacquisition mode currentlybeing contemplated, the correlation power for each tap is immediatelymeasured. In this configuration, it is advantageous to use a separateindependent channel for code phase verification.

In particular as shown in FIG. 23, Segment #1 is applied to multiplesatellite tracking channels including SatTRAK channels 38, 40, 42 and 44and so on for tracking SVs 1 through 11. Segments #2 through #186 areprocessed in sequence in the same manner.

CodePhase Verification SatTRAK channel 300, which was shown above inFIG. 11 as the SatTRAK channel used for tracking SV 12, is used in thefast reacquisition mode rather than the tracking mode to verify the codephase for each SV in turn. The task of verifying the code phase isdescribed above and refers to search for a direct path signal receivedalong a shorter path than the path of the signal being tracked.

In operation, during the first ms, the 11 ½ half bit sample of Segment#1 is processed in turn in CodePhase Verification SatTRAK channel 300with the code phase adjusted so that the prompt correlation for thesatellite signal currently tracked is correlated at one of the largerdelays, such as at tap #22. The delay theories being tested at taps #1through #21 are then the conventional early correlation at tap #21 andprogressively earlier times from tap #21 back to tap #1.

As an example, multipath signal 231 from SV #1 may inadvertently betracked in SatTRAK channel 38. In SatTRAK channel 38, the code phasedelays for the 22 taps in SatTRAK channel 38 would be adjusted so thatthe prompt correlation would occur at tap #2. During an 1 ms timeperiod, the repetition period for a full 1023 bit sequence of the C/Acode, CodePhase Verification SatTRAK channel 300 would be used to verifythat no earlier, potentially direct path signal, was also available.

In operation, the code phase of CodePhase Verification SatTRAK channel300 is adjusted so that the peak of the signal being tracked, in thisexample the peak of multipath signal 231, is tracked in tap #22. Asshown in FIG. 23, after accumulation over 186 segments, a correlationpower magnitude of 4 m representing the peak of multipath signal 231, isaccumulated at tap #22 and the half power point is shown as a magnitudeof 2 at tap #21. In addition, peak 230 of the direct signal isaccumulated at tap #4 with a magnitude of 6, while the half power pointsare shown at magnitudes of 3 for the early and late correlation powersat taps 3 and 5, respectively.

During the next ten ms time periods, the powers for the correlationproducts at each tap for each of the remaining SVs 2 through 11 aretested. For each SV, the earliest peak is selected as the direct pathsignal and the code phase for that SV is adjusted according. The processmay then be repeated.

As noted above with regard to FIG. 22, it may be advantageous to trackthe multipath reflection signal in order to model the direct ormultipath signal to either minimize interference when the differentialpath delay is on the order of about 1.5 ½ chips or less or to continueto track a temporarily obscured direct path signal. These tasks may alsobe conveniently accomplished in CodePhase Verification SatTRAK channel300, for one SV per ms.

Referring now to FIG. 24, a block diagram of an alternate embodiment ofthe GPS car navigation system depicted in FIG. 2 used for improvednavigation during reduced satellite visibility is shown.

As noted above, GPS receivers are preferably operated with a minimum of3 or 4 satellites distributed across the visible sky in order todetermine, or at least estimate, the four necessary unknowns typicallyincluding x_(user), y_(user) and z_(user) which provide three orthogonalcoordinates to locate the user as well as t_(user) which provides therequired satellite time. In the embodiment shown in FIG. 24, the fourunknowns are specified as a_(user), c_(user), z_(user) and t_(user). Thethree orthogonal user coordinates are a_(user), which locates the userin terms of the distance along the currently identified heading ortrack, c_(user), which locates the user in terms of the cross trackdistance of the user from the currently identified heading or track, andz_(user) which represents the altitude of the user, conventionally interms of the vertical distance above or below sea level.

As depicted in FIG. 24, GPS car navigation system 400 processessatellite signals in ASIC 102 received in satellite receiver section 36from GPS antenna 28 to track all currently visible satellites insatellite specific tracking channels such as SatTRAK channels 38, 40, 42and 44, the outputs of which are applied to SatProcessor 46. Anavigation solution may then be produced in NavProcessor 402 whichcreates position model 403 of the four unknowns, such as internal clockmodel 54, altitude estimate 56, c_(est) 404 and a_(est) 406. The use ofc_(est) 404 and a_(est) 406 has been found to be advantageous even whenmore than one satellite is in view.

GPS car system module 26 is also provided with data related to the thencurrent—and expected future—physical environment of car 10 from, forexample, Route Data Base 52 which includes information about the routingin the form of roadways and turns between roadways, as well as actual orestimated roadway width. The estimated roadway width may simply be adefault value representing a common roadway width such as the width of atwo lane city street or highway if no other information is thenavailable.

Solutions for all 4 unknowns of position information may be derived whensignals from 4 satellites in a proper geometric configuration are view.When signals from only 3 visible satellites are available for suitableprocessing, the z_(user) solution may be replaced by z_(user) 56solution derived from an elevation estimate or default in what isconventionally called the altitude hold mode of processing. Changes inelevation occur relatively slowly in terrestrial navigation so that thedegradation of position accuracy during altitude hold is oftenacceptable.

When signals from only 2 suitable satellites are available, the c_(user)position information is replaced by c_(est) which may be derived fromRoute Data Base 52 or otherwise estimated in what has been referred toherein as the cross track hold mode of processing. The maximum physicalcross track distance, that is, the width of the roadway, is typicallysmaller than the position accuracy currently available with the GPSsystem and therefore any position information degradation resulting fromcross track hold is usually acceptable as long as the vehicle isprogressing along a known track or direction.

Referring now to FIG. 25A, if route data from Route Data Base 52 oranother source is being used, predicted track 408 may represent actualroadway 409, which is shown to extend for example in a first directionfrom point 410 to turn 412 after which actual roadway 409, and thereforepredicted track 408, turns about 30° toward the right. A similarsituation occurs when an intentional turn is made, for example, whenexiting a highway.

Referring now to FIG. 25B, if detailed roadway or track data is notbeing used, the default estimate for predicted track 408 may simply bethe current heading. That is, as long as the vehicle including GPS carnavigation system 400 is proceeding along actual roadway 409 from point410 to turn 412, predicted track 408 follows actual roadway 409 and nocross track error occurs. After turn 412, however, if predicted track408 is merely estimated from the heading of the vehicle between point410 and turn 412, predicted track 408 would continue along the sameoriginal direction while actual roadway 409 turns toward the right.

In the situation shown in FIG. 25A, cross track hold may successfully beused, without substantial accuracy degradation, both before and afterturn 412. However, in the situation depicted in FIG. 25B after turn 412,the actual path of actual roadway 409 is not known and is merelyestimated by the previous vehicle heading so that substantial crosstrack error may occur. In particular, the cross track error at turn 412is zero but increases to cross track error distance 414 when the vehiclereaches point 416 along actual roadway 409. Thereafter, when GPS carnavigation system 400 reaches point 420 on actual roadway 409, the crosstrack error reaches cross track error distance 418.

One way to effectively continue to use cross track hold in the situationdepicted in FIG. 25B, in which predicted track 408 is merely estimatedfrom the current heading, is to utilize turn detector 66 shown in FIG.2, to detect the occurrence of a turn. The turn detection indication maybe used in conjunction with turn comparator 68 and Route Data Base 52 tocorrect or update predicted track 408 to correspond to the actual pathof actual roadway 409 or merely to require a re-estimation of predictedtrack 408 by using the then current heading after the turn. Similarly, aless desirable but simpler approach is to use timer 422 to causepredicted track 408 to be periodically re-estimated from the thencurrent heading.

A better alternative is shown in FIG. 24 in which steady state detector424 may be used as an alternative to, or in addition to, turn detector66. Steady state detector 424 may be simply a type of turn detector,such as a magnetic compass, or a more sophisticated device such as aninertial navigation system. In any event, steady state detector 424serves to indicate that the vehicle is no longer maintaining steadystate conditions, that is, no longer following a straight line orcontinuing along a smooth curve. The output of steady state detector 424is applied to NavProcessor 402 to indicate that predicted track 408 isno longer accurate because the vehicle has changed direction.

In accordance with a preferred embodiment of the present invention, uponan indication from steady state detector 424 that a change from steadystate conditions has occurred during cross track hold, if more than onesatellite signal is in view NavProcessor 402 automatically switches fromcross track hold to clock hold. In other words, upon an indication thata cross track error may exists, the current clock estimate is maintainedduring a brief period in which the cross track estimate is updated.

The length of time during which clock hold may be maintained withoutsubstantial degradation of position accuracy is a function of theaccuracy, or drift, of the real time clock used in GPS car navigationsystem 400. This accuracy may be predicted and is probably good enoughto use for periods at least on the order of about 30 to 60 seconds. Afirst step in increasing the length of time during which clock hold maybe maintained without unacceptable position degradation is to maintain amodel of the error of the real time clock.

Real time clock error model 426 serves to monitor the drift of real timeclock 428 shown in FIG. 12. The clock drift, compared to the actual timeas determined from the satellites, is determined as a function of timeso that further drift may be predicted. Some of the factors whichcontribute to this drift are linear and predictable so that someportions of the clock drift may be accurately modeled and the clockadjusted to compensate for that drift. Other factors which contribute tothe clock drift are unpredictable. That is, even after correcting theclock for errors detectable in comparison to satellite time, theaccuracy of real time clock 428 may only be improved to a certain level.The inaccuracy of the clock model, resulting from the random andunpredictable factors, determines the length of time that clock hold maybe used without an unacceptable level of accuracy degradation.

Real time clock error model 426 may then be used to set the length ofthe period during which clock hold may be used so that cross track holdcan be released and cross track error minimized or eliminated. Inoperation, real time clock error model 426 monitors real time clock 428to determine the level of unpredictable, that is uncorrectable, clockdrift while SatProcessor 46 corrects real time clock 428 in response tosignals from the GPS satellites. Thereafter, when there are only twovisible satellites, the cross track hold mode is instituted and steadystate detector 424 monitors the progress of the vehicle to determinewhen a turn or other even changes is indicated by a change from steadystate conditions.

Thereafter cross track hold is released and clock hold is instituted tocorrect any cross track error. Thereafter, in accordance with timer 422,clock hold is released and cross track hold is re-instituted. Crosstrack hold is then maintained while only two satellites are visible withusable signals until the next time that steady state detector 424indicates the possible existence of a substantial cross track error.Alternatively, during long periods of cross track hold, clock hold maybe used periodically in accordance with timer 422 to permit reduction ofany accumulated cross track error. In this manner, the best possiblenavigation solution may be obtained from signals from two satellites bycycling between two hold states such as cross track and clock hold. Thetime in each hold state is limited in accordance with indications orpredictions of unacceptable deviation from the held or modeled value.

In most typical operating conditions in terrestrial navigation, thewidth of the roadway, waterway or airway—and the likelihood of steadystate motion—both contribute to a preference for cross track hold overclock hold, especially in light of the drift errors in currentlyavailable real time clocks used for GPS receivers. The periodic cyclingbetween cross track and clock hold provides the most accurate anddependable navigation solutions for two visible satellites. If thesecond satellite also becomes unavailable so that signals from only asingle satellite remain useful, clock hold may be used in conjunctionwith cross track hold for single satellite navigation.

Referring now again to FIG. 12, power consumption is a critical issuefor many terrestrial spread spectrum receivers, including GPS receivers,particularly for battery powered receivers. Many battery poweredreceivers will be used in environments in which the battery drain due tothe receiver is nominal, and/or may be conveniently replenished, such asin a vehicle. Many other battery powered receivers, referred to hereinas hand held units for convenience, must rely solely on their batteriesfor power and be re-powered on a regular basis by recharging thebatteries or replacing them. In addition, the nature of the use ofdevices of this type makes a reasonably long battery life important.

Conventional devices may be powered down, that is turned off, so thatbattery drain in minimal. However, the time required to power up andprovide a reasonable navigation solution is often unsatisfactory. Forexample, when a conventional receiver is powered up after just beingpowered down it may be able to easily reacquire the satellites it waspreviously tracking but such reacquisition takes at least 2 to 3seconds. This time lag is too long to permit powering down betweenposition fixed in most applications. In a vehicle, a user would prefernot to wait several seconds after requesting a position fix for thereceiver to provide an updated navigation solution.

Further, if a receiver has been powered down for more than a fewseconds, the accumulated time errors will often result in the need for asearch in order to lock onto the satellite signals unless a high quality(and therefore expensive) real time clock, or other source of accuratetime information, is provided. A satellite signal search may take 15minutes if the receiver has not been powered up for awhile.

In accordance with the present invention, however, energy savingtechniques have been employed to permit battery operated, hand-held orsimilar receivers to be operated with minimal battery energyrequirements and to provide instantaneous, or at least perceptiblyinstantaneous, position fixes and navigation solutions when the unit ispowered up or when a position fix is requested. By the terminstantaneous, or perceptibly instantaneous, what is meant is arelatively short delay time on the order of one quarter to one half of asecond between the time that the unit is activated and the time the userreceives the position fix so that the user is not made aware of aresponse time delay.

There are two primary battery saving modes of operation, the push to fixor sleep mode and the reduced power continuous navigation mode.

In the push to fix mode, when a navigation solution or position fix isrequired, the user pushes a button on the unit and a position fix isdisplayed in a sufficiently short time that the user is not bothered bythe time required to reacquire and provide the navigation solution. Thepush to fix mode may therefore provide a perceptually instantaneousnavigation solution when the push to fix control is activated. Duringthe remainder of the time, the receiver operates in a sleep mode inwhich minimum power is used. During the sleep mode, however, theeffective clock error has been modelled so that clock accuracymaintenance is performed automatically to keep the unpredictable clockerror below a predetermined magnitude so that the receiver may bere-energized to perform clock maintenance with a minimum of wastedenergy.

In the reduced power continuous operation mode, a perceptuallyconstantly updated navigation solution is provided. The majority of theenergy using portions of the receiver system are not powered for asubstantial fraction of each second. For example, as will be describedbelow, the present invention may be operated in a mode in which the fulloperation of the receiver is used for only 200 milliseconds per second,saving about 80% of the battery energy that would otherwise be usedduring the remaining 800 milliseconds of each second.

As shown in FIG. 12, GPS receiver system 200 may be dividing up intoseveral major subsystems including, for example, RF processing subsystem214 including the antenna input and RF signal preconditioning filteringand pre-amp stages, an IF filter as well as the crystal oscillator foran accurate clock or counter, together with a signal processing stagebased on ASIC GSP1 202 and digital section 430 which includes thedigital computer facilities such as SRAM 206, ROM 208 and CPU 101,interconnected by data and address busses 210 and 212, as well as realtime clock 428.

In accordance with the present invention, RF processing subsystem 214and ASIC GSP1 202 are powered down into a so-called sleep mode for asubstantial portion of the time while digital section 430 remainspowered to maintain the operation of real time clock 428. In manysystems, it may be desirable to maintain crystal 224 in a ready tooperate condition during the “off” or sleep state, by for example,keeping it warm in a temperature controlled environment.

In the push to fix mode, the duration of the permissible power down or“off” time during the sleep mode, that is the time interval betweenclock accuracy maintenance operations, is dependent upon the level ofunpredictable, or un-modelable, drift of real time clock 428. In atypical application, the crystal used in real time clock 428 will be arelatively inexpensive crystal on the order of the quality of crystalsused in a personal computer. Such crystals may provide a time resolutionof 30 micro seconds or better and be modelable to hold time to withinone half millisecond in perhaps 50 seconds.

In order to maximize the sleep or “off” time in a push-to-fix mode ofoperation, the drift of real time clock 428 is measured and modeledagainst a more accurate time base as provided by crystal 224 in RFprocessing subsystem 214 and/or from the signals from the satellites. Itmay be convenient to model the clock error of real time clock 428 sothat the elapsed time during which the unpredictable changes in realtime clock 428 occur can be determined. This modeling may beaccomplished a priori, by estimating, or in accordance with a preferredembodiment of the present invention, be continuously determined duringoperation so that the full accuracy of real time clock 428 is used.

If it is determined that real time clock 428 drifts in a predictablefashion, real time clock 428 may be updated by digital section 430 on aregular basis to compensate for the drift. The period for updating maythen be lengthened so that the unpredictable (and thereforeun-modelable) error never exceeds a predetermined amount, for example,one half millisecond. That is, if the maximum permissible error isselected to be one half millisecond, then the determined period for themaximum off time depends on how long it takes the clock to drift by onehalf millisecond in an unpredictable way.

In the sleep mode, at the end of the off time, CPU 101 causes the powerto be reapplied to RF processing subsystem 214 and to ASIC GSP1 202. RFprocessing subsystem 214 attempts to continue tracking and/or reacquirea selected satellite. The selected satellite may conveniently be thesatellite with the strongest, or otherwise most usable, signal asdetermined from the previous “on” time. The “off” time has been selectedso that the signals from the selected satellite are within a known timeoffset and are therefore easily reacquired.

In accordance with a preferred embodiment of the present invention,approximately 240 correlations may be performed, accumulated andcompleted during each millisecond, that is, during each repetition ofthe C/A code. These 240 correlations each represent one half chip oftime. If the clock error represents less than about plus or minus 60chips, which may be on the order of plus or minus 10 miles inpseudorange, tracking occurs during the first millisecond. That is,usable data is immediately collected. In particular, if the clock erroris within plus or minus 120 half chips, one of the 240 correlations willin fact be the prompt correlation. At the end of the first millisecond,the data from the prompt correlation may be used in the usual way totrack the selected satellite and thereby determine the clock error.Therefore, at the end of the first millisecond of clock maintenanceoperation, the clock error may be corrected and the pseudorange to the“best” or selected satellite redetermined.

During the next and subsequent 1 ms periods, normal tracking of all, orat least most, of the other satellites remaining visible may be resumedbecause the error in real time clock 428 has been corrected.

In this manner, clock maintenance is automatically performed at least asoften as required by the actual drift of the clock so that the length ofoperating time required to resume tracking may be controlled. Theduration of the “off” time can be controlled in general as a function ofthe quality of real time clock 428. For any particular level of clockerror, the amount of power required for resumption of tracking may becontrolled in part by the number of correlations used. As morecorrelations are used, more energy is consumed, but longer “off” timesmay be employed.

In the presently preferred embodiment it has been determined that a 50second off time would be appropriate with a convenient quality level ofclock crystal for real time clock 428. The exact length of off time maybe determined by clock error modeling during action operation of thereceiver, as noted above. At the end of the 50 second “off” period, GPSreceiver system 200 is powered up and can immediately resume tracking atleast the first satellite during the first millisecond and all availablesatellites thereafter. If GPS receiver system 200 was powered up as aresult of the need for clock accuracy maintenance, no further trackingis required and the “off” or battery energy save state may be resumed assoon as the clock error is corrected by tracking the first satellite.

If satellite tracking of the selected satellite is not resumed duringthe first millisecond for clock accuracy maintenance, the total timerequired to reacquire the best satellite will typically be less than 9milliseconds because all 1023 possible delay theories can be tested withabout 9 passes of the 240 delays per pass.

If, in addition to clock error maintenance, a navigation solution isrequired, normal operation of GPS receiver system 200 may be continuedfor as long as required after a clock maintenance operation to completethe navigation solution.

In operation, after normal satellite tracking, push to fix operation maybe instituted and the receiver will enter the sleep mode for the perioddetermined by the clock error model to permit the clock to remainaccurate to within a fix amount, say half a millisecond. At the end ofthe sleep mode period so determined, clock maintenance occurs in whichthe receiver wakes up long enough to correct real time clock 428.Thereafter, the sleep mode is resumed.

Upon receipt of a push to fix request for a navigation solution, a clockmaintenance operation is performed to correct real time clock 428 andthen normal tracking is resumed for all satellites being tracked. Thenavigation solution may then be determined in the usual manner and thesleep mode resumed.

In the reduced energy, continuous operation mode, the sleep mode isengaged on a periodic basis, such as for 800 milliseconds in eachsecond. The modeled clock drift is sufficiently small at the end of thesleep mode so that normal tracking may be automatically resumed. Duringthe next 200 milliseconds, satellite tracking is then resumed, clockcorrections are made, and the navigation solution determined.

During the next succeeding seconds, the 800 millisecond sleep modecontinues to be alternated with a 200 millisecond tracking mode, therebysubstantially reducing the energy requirements for apparently normal,continuous operations. During the 800 millisecond sleep period, digitalsection 430 or at least a substantial portion thereof remains active.Assuming for convenience that the energy used by the RF, signalprocessing and digital processing subsystems are approximately equal,the energy savings is therefore on the order of about two thirds of 80%of the full operation energy budget for an approximate savings of abouthalf while updating the position fix once per second.

In many hand held applications, continuous operation may require aposition fix at time intervals of substantially greater than one second,say for example 5 seconds. The operation of the RF and signal processingsections for only about 200 ms each 5 seconds provides a tremendousincrease in operating life for any particular set of batteries.

Referring now to FIG. 26, these modes of operation may be combined inlow power consumption receiver 432 which operates in an energyconserving continuous, as well as push to fix, modes. Operations beginas described above in full time acquisition and then tracking modes,indicated as step 434. In the preferred embodiment, push to fix inquiry436 is made. If push to fix operation is not required, the receiver isoperated in a sleep mode for a fixed period of time, such as 800 ms,under the direction of step 438. Thereafter a fixed period of tracking,for example 200 ms, is accomplished under step 440. Operation cyclesbetween steps 438 and 440 until push to fix operation is required.

When push to fix operation is begun, sleep mode 442 is entered untilinquiry 444 determines that maximum allowable clock error has occurred.As noted above, the period of time in which this clock error occurs, oris modelled to occur, depends upon the maximum allowable error which inturn depends upon the number of correlations available per unit time aswell as the length of time permitted for resumption, or reacquisition,of tracking. In the presently preferred embodiment using 240correlations per millisecond and requiring clock drift to be limited toplus or minus one half millisecond, a sleep period of up to 50 secondsmay be allowed.

When the sleep period based on maximum allowable clock error is over,the resumption of tracking in step 446 is begun for the selectedsatellite using the maximum number of correlators available. When a lock448 on the selected satellite's signal has been achieved, the real timeclock and/or the corrected clock model is updated under step 450. If afix (inquiry 452) is required, tracking is then resumed under step 454for all satellites using the correlations in a time division multiplexedfashion as described above. If a fix is not presently required, andinquiry 436 indicates that the push to fix mode is to continue, thereceiver resumes the sleep mode under step 442 until maximum clock errorreoccurs or is predicted to reoccur, for example, at the expiration ofan additional 50 seconds.

Having now described the invention in accordance with the requirementsof the patent statutes, those skilled in this art will understand how tomake changes and modifications in the present invention to meet theirspecific requirements or conditions. Such changes and modifications maybe made without departing from the scope and spirit of the invention asset forth in the following claims.

What is claimed is:
 1. A system for operating a GPS C/A code receivercomprising: a plurality of channel means, each comprising, means forforming x multibit digital segment values per C/A code period, eachmultibit digital segment value representing a sequential code segment ofa received composite of satellite signals; and a plurality ofcorrelating means for correlating each digital segment value with nsatellite specific sets of in differently time delayed segments of C/Acode modulation to form at least n times in time delay specificcorrection values, wherein x, m, and n are each prime factors of anumber of code chips per C/A code period.
 2. The system of claim 1wherein m is greater than the number of bits in each multibit of claim 1wherein each bit of the multibit digital.
 3. The system of claim 1wherein each bit of the multibit digital segment value represents aninteger fraction of a C/A code chip.
 4. The system of claim 1 whereinthe correlating means comprises means for tracking different satellitesby selecting the satellite specific sets to represent n differentsatellites.
 5. The system of claim 1 wherein the correlating meanscomprises means for tracking different satellites by selecting more thanone of the satellite specific sets to represent the same satellite. 6.The system of claim 5 wherein the lime delay segments of the satellitespecific sets representing the same satellite are sequential.
 7. Thesystem of claim 5 wherein the time delay segments of the satellitespecific sets representing the same satellite are interlaced.
 8. Thesystem of claim 5 wherein the differential time delay of the segments ofthe satellite specific sets representing the same satellite representless than a maximum expected time delay error for a temporarily obscuredsatellite in an urban environment.
 9. The system of claim 1 wherein thecorrelating means comprises means for tracking different satellites byselecting the satellite specific sets to represent an integer fractionof n different satellites.
 10. The system of claim 1 wherein thecorrelating means comprises means for tracking n/2 satellites byselecting the satellite specific sets to represent n/2 differentsatellites.
 11. The system of claim 1 wherein the con-elating means i8adapted to: acquire a satellite by selecting the satellite specific setsto represent the same satellite; and repeat the correlation for the samesatellite with a different set of time delayed segments.
 12. The systemof claim 1 further comprising means for forming series of m/2differently time delayed segments by sequentially changing one bit of aprevious segment to faint the next segment.
 13. The system of claim 1wherein the forming means comprises: means for sampling the receivedcomposite at a first bit rate; and means for digitally filtering thefirst composite to form the digital segment values at a bit ratesubstantially lower than the first bit rate.
 14. The system of claim 1further comprising means for interrupting the correlating means for aseries of code periods to reduce receiver energy consumption.
 15. Asystem for tracking the movement of an object, said system comprising: amulti-channel GPS C/A code receiver associated with the object, whereineach of a plurality of channels is adapted to, form x multibit digitalsegment values per C/A code period, each multibit digital segment valuerepresenting a sequential code segment of a received composite ofsatellite signals; and correlate each digital segment value with asatellite specific sets of in differently time delayed segments of C/Acode modulation to form at least n times m time delay specificcorrelation values, wherein x, m, and n are each prime factors of anumber of code chips per C/A code period; and means for determiningnavigation information from the correlation values.
 16. The system ofclaim 15 wherein the determining means comprises means for comparing themagnitudes for two equal correlation values to the magnitude of acorrelation value therebetween to select a prompt delay.
 17. The systemof claim 16 wherein the comparing means comprises means for selectingthe prompt delay to be more than halfway between the time delaysrepresented by the equal correlation values when the magnitude of theequal correlation products is equal to less than the half of a peakcorrelation value therebetween.
 18. The system of claim 16 wherein thecomparing means comprises means for selecting the prompt delay to beless than halfway between the time delays represented by the equalcorrelation values when to magnitude of the equal correlation productsis equal to more than half of a peak correlation value therebetween. 19.A method of operating a GPS C/A code receiver comprising, in each of aplurality of receiver channels: forming x multibit digital segmentvalues per C/A code period, each multibit digital segment valuerepresenting a sequential code segment of a received composite ofsatellite signals; correlating each digital segment value with nsatellite specific sets of m differently time delayed segments of C/Acode modulation to form at least n times m time delay specificcorrelation values, wherein x, m, and n are each prime factors of anumber of code chips per C/A code period; and accumulating thecorrelation values in a n times m matrix.